US5932940A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Microturbomachinery
Assignee: Massachusetts Institute of Technology
•
Filing: 1996-11-15
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Granted: 1999-08-03
•
Expires: 2016-11-15
Abstract
Abstract The invention provides a micro-gas turbine engine and associated microcomponentry. The engine components, including, e.g., a compressor, a diffuser having diffuser vanes, a combustion chamber, turbine guide vanes, and a turbine are each manufactured by, e.g., microfabrication techniques, of a structural material common to all of the elements, e.g., a microelectronic material such as silicon or silicon carbide. Vapor deposition techniques, as well as bulk wafer etching techniques, can be employed to produce the engine. The engine includes a rotor having a shaft with a substantially untapered compressor disk on a first end, defining a centrifugal compressor, and a substantially untapered turbine disk on the opposite end, defining a radial inflow turbine. The rotor is preferably formed of a material characterized by a strength-to-density ratio that enables a rotor speed of at least about 500,000 rotations per minute. An annular, axial-flow combustion chamber is provided that is located axially between the compressor and turbine disks and that has a ratio of annular height to axial length of at least about 0.5. The micro-gas turbine engine can be configured with an integral microgenerator as a source of electrical power, and can be employed for a wide range of power, propulsion, and thermodynamic cycle applications.
Inventors
- 👤 Alan H. Epstein
- 👤 Stephen D. Senturia
- 👤 Ian A. Waitz
- 👤 Jeffrey H. Lang
- 👤 Stuart A. Jacobson
- 👤 Fredric F. Ehrich
- 👤 Martin A. Schmidt
- 👤 G. K. Ananthasuresh
- 👤 Mark S. Spearing
- 👤 Kenneth S. Breuer
- 👤 Steven F. Nagle
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-29 15:02
CPC Classifications
F; F23; F23R; F23R3/00; F23R3/42; F01; F01D; F01D15/00; F01D15/06; F01D25/00; F01D25/18; F01D25/20; F01D5/00; F01D5/12; F01D5/28; F01K; F01K13/00; F02; F02C; F02C3/00; F02C3/04; F02C3/045; F02C3/05; F02K; F02K9/00; F02K9/42; F02K9/44; F02K9/46; F02K9/48; F05; F05D; F05D2220/00; F05D2220/50; F05D2230/00; F05D2230/10; F05D2230/14; F05D2250/00; F05D2250/80; F05D2250/82; F05D2250/84; F05D2300/00; F05D2300/20; F05D2300/22; F05D2300/226; F05D2300/2261; F05D2300/228; F05D2300/2283; F05D2300/60; F05D2300/607; F23C; F23C2900/00; F23C2900/03001
Claims Analysis
Total Claims: 83
Claim 1
Independent Claim
143 words
A gas turbine engine comprising: a compressor having an engine inlet port and a rotatable compressor disk for compressing inlet air; a diffuser located to receive compressed air from the compressor and produce a corresponding rise in static air pressure; a combustor comprising a combustion chamber located to receive the compressed air from the diffuser through a combustor inlet to combust the compressed air with a fuel; a plurality of turbine nozzle guide vanes located to receive combusted air exhausted from the combustor; a turbine having a rotatable turbine disk located to receive combusted air from the turbine nozzle guide vanes, and having an engine exhaust port; and bearing surfaces of the rotatable elements; wherein the compressor, diffuser, combustion chamber, turbine nozzle guide vanes, and turbine elements and the bearing surfaces each substantially comprise a structural material common to all of the elements.
Claim 2
Dependent Claim
143 words
A gas turbine engine comprising: a compressor having an engine inlet port and a rotatable compressor disk for compressing inlet air; a diffuser located to receive compressed air from the compressor and produce a corresponding rise in static air pressure; a combustor comprising a combustion chamber located to receive the compressed air from the diffuser through a combustor inlet to combust the compressed air with a fuel; a plurality of turbine nozzle guide vanes located to receive combusted air exhausted from the combustor; a turbine having a rotatable turbine disk located to receive combusted air from the turbine nozzle guide vanes, and having an engine exhaust port; and bearing surfaces of the rotatable elements; wherein the compressor, diffuser, combustion chamber, turbine nozzle guide vanes, and turbine elements and the bearing surfaces each substantially comprise a structural material common to all of the elements.
Claim 3
Dependent Claim
126 words
A gas turbine engine comprising: a compressor having an engine inlet port and a rotatable compressor disk for compressing inlet air; a diffuser located to receive compressed air from the compressor and produce a corresponding rise in static air pressure; a combustor comprising a combustion chamber located to receive the compressed air from the diffuser through a combustor inlet to combust the compressed air with a fuel; a plurality of turbine nozzle guide vanes located to receive combusted air exhausted from the combustor; and a turbine having a rotatable turbine disk located to receive combusted air from the turbine nozzle guide vanes, and having an engine exhaust port; wherein the compressor diffuser, combustion chamber, turbine nozzle guide vanes, and turbine elements each substantially comprise silicon carbide.
Claim 4
Dependent Claim
126 words
A gas turbine engine comprising: a compressor having an engine inlet port and a rotatable compressor disk for compressing inlet air; a diffuser located to receive compressed air from the compressor and produce a corresponding rise in static air pressure; a combustor comprising a combustion chamber located to receive the compressed air from the diffuser through a combustor inlet to combust the compressed air with a fuel; a plurality of turbine nozzle guide vanes located to receive combusted air exhausted from the combustor; and a turbine having a rotatable turbine disk located to receive combusted air from the turbine nozzle guide vanes, and having an engine exhaust port; wherein the compressor diffuser, combustion chamber, turbine nozzle guide vanes, and turbine elements each substantially comprise silicon carbide.
Claim 5
Dependent Claim
16 words
The gas turbine engine of claim 2 wherein the silicon carbide comprises vapor deposited silicon carbide.
Claim 6
Dependent Claim
125 words
A gas turbine engine comprising: a compressor having an engine inlet port and a rotatable compressor disk for compressing inlet air; a diffuser located to receive compressed air from the compressor and produce a corresponding rise in static air pressure; a combustor comprising a combustion chamber located to receive the compressed air from the diffuser through a combustor inlet to combust the compressed air with a fuel; a plurality of turbine nozzle guide vanes located to receive combusted air exhausted from the combustor; and a turbine having a rotatable turbine disk located to receive combusted air from the turbine nozzle guide vanes, and having an engine exhaust port; wherein the compressor, diffuser, combustion chamber, turbine nozzle guide vanes, and turbine elements each substantially comprise silicon.
Claim 7
Dependent Claim
125 words
A gas turbine engine comprising: a compressor having an engine inlet port and a rotatable compressor disk for compressing inlet air; a diffuser located to receive compressed air from the compressor and produce a corresponding rise in static air pressure; a combustor comprising a combustion chamber located to receive the compressed air from the diffuser through a combustor inlet to combust the compressed air with a fuel; a plurality of turbine nozzle guide vanes located to receive combusted air exhausted from the combustor; and a turbine having a rotatable turbine disk located to receive combusted air from the turbine nozzle guide vanes, and having an engine exhaust port; wherein the compressor, diffuser, combustion chamber, turbine nozzle guide vanes, and turbine elements each substantially comprise silicon.
Claim 8
Dependent Claim
126 words
A gas turbine engine comprising: a compressor having an engine inlet port and a rotatable compressor disk for compressing inlet air; a diffuser located to receive compressed air from the compressor and produce a corresponding rise in static air pressure; a combustor comprising a combustion chamber located to receive the compressed air from the diffuser through a combustor inlet to combust the compressed air with a fuel; a plurality of turbine nozzle guide vanes located to receive combusted air exhausted from the combustor; and a turbine having a rotatable turbine disk located to receive combusted air from the turbine nozzle guide vanes and having an engine exhaust port; wherein the compressor, diffuser, combustion chamber, turbine nozzle guide vanes, and turbine elements each substantially comprise silicon nitride.
Claim 9
Dependent Claim
126 words
A gas turbine engine comprising: a compressor having an engine inlet port and a rotatable compressor disk for compressing inlet air; a diffuser located to receive compressed air from the compressor and produce a corresponding rise in static air pressure; a combustor comprising a combustion chamber located to receive the compressed air from the diffuser through a combustor inlet to combust the compressed air with a fuel; a plurality of turbine nozzle guide vanes located to receive combusted air exhausted from the combustor; and a turbine having a rotatable turbine disk located to receive combusted air from the turbine nozzle guide vanes and having an engine exhaust port; wherein the compressor, diffuser, combustion chamber, turbine nozzle guide vanes, and turbine elements each substantially comprise silicon nitride.
Claim 10
Dependent Claim
127 words
A gas turbine engine comprising: a compressor having an engine inlet port and a rotatable compressor disk for compressing inlet air; a diffuser located to receive compressed air from the compressor and produce a corresponding rise in static air pressure; a combustor comprising a combustion chamber located to receive the compressed air from the diffuser through a combustor inlet to combust the compressed air with a fuel; a plurality of turbine nozzle guide vanes located to receive combusted air exhausted from the combustor; and a turbine having a rotatable turbine disk located to receive combusted air from the turbine nozzle guide vanes, and having an engine exhaust port; wherein the compressor, diffuser, combustion chamber, turbine nozzle guide vanes, and turbine elements each substantially comprise a semiconductor material.
Claim 11
Dependent Claim
127 words
A gas turbine engine comprising: a compressor having an engine inlet port and a rotatable compressor disk for compressing inlet air; a diffuser located to receive compressed air from the compressor and produce a corresponding rise in static air pressure; a combustor comprising a combustion chamber located to receive the compressed air from the diffuser through a combustor inlet to combust the compressed air with a fuel; a plurality of turbine nozzle guide vanes located to receive combusted air exhausted from the combustor; and a turbine having a rotatable turbine disk located to receive combusted air from the turbine nozzle guide vanes, and having an engine exhaust port; wherein the compressor, diffuser, combustion chamber, turbine nozzle guide vanes, and turbine elements each substantially comprise a semiconductor material.
Claim 12
Dependent Claim
141 words
A gas turbine engine comprising: a compressor having an engine inlet port and a rotatable compressor disk for compressing inlet air; a diffuser located to receive compressed air from the compressor and produce a corresponding static rise in air pressure; a combustor comprising a combustion chamber located to receive the compressed air from the diffuser through a combustor inlet to combust the compressed air with a fuel; a plurality of turbine nozzle guide vanes located to receive combusted air exhausted from the combustor; and a turbine having a rotatable disk located to receive combusted air from the turbine nozzle guide vanes, and having an engine exhaust port; wherein the compressor, diffuser, combustion chamber, turbine nozzle guide vanes, and turbine elements each comprise a microfabricated element, and a ratio of engine radial height to engine axial length is at least about 1.
Claim 13
Dependent Claim
141 words
A gas turbine engine comprising: a compressor having an engine inlet port and a rotatable compressor disk for compressing inlet air; a diffuser located to receive compressed air from the compressor and produce a corresponding static rise in air pressure; a combustor comprising a combustion chamber located to receive the compressed air from the diffuser through a combustor inlet to combust the compressed air with a fuel; a plurality of turbine nozzle guide vanes located to receive combusted air exhausted from the combustor; and a turbine having a rotatable disk located to receive combusted air from the turbine nozzle guide vanes, and having an engine exhaust port; wherein the compressor, diffuser, combustion chamber, turbine nozzle guide vanes, and turbine elements each comprise a microfabricated element, and a ratio of engine radial height to engine axial length is at least about 1.
Claim 14
Dependent Claim
34 words
The gas turbine engine of claim 7 wherein the wherein the compressor, diffuser, combustion chamber, turbine nozzle guide vanes, and turbine elements each substantially comprise a structural material common to all of the elements.
Claim 15
Dependent Claim
18 words
The gas turbine engine of claim 7 wherein the compressor and turbine each comprise single crystal silicon disks.
Claim 16
Dependent Claim
18 words
The gas turbine engine of claim 9 wherein the compressor and turbine each comprise microfabricated bulk-etched silicon wafers.
Claim 17
Dependent Claim
16 words
The gas turbine engine of claim 7 wherein the combustion chamber comprises microfabricated vapor-deposited silicon carbide.
Claim 18
Dependent Claim
16 words
The gas turbine engine of claim 7 wherein compressor and turbine each comprise silicon carbide disks.
Claim 19
Dependent Claim
19 words
The gas turbine engine of claim 12 wherein the compressor and turbine each comprise microfabricated bulk-etched silicon carbide wafers.
Claim 20
Dependent Claim
155 words
A gas turbine engine comprising: a rotor comprising a shaft having a substantially untapered compressor disk on a first end of the shaft with compressor blades defining a centrifugal compressor and a substantially untapered turbine disk on an opposite end of the shaft with turbine blades defining a radial inflow turbine, the rotor further comprising a material characterized by a strength-to-density ratio enabling a rotor speed of at least about 500,000 rotations per minute; an annular, radial out-flow diffuser located radially outward of the compressor disk for receiving compressed air from the compressor; an annular combustor located radially outward of the rotor shaft, having a combustor inlet radially outward of the diffuser, and having an exhaust outlet radially outward of the turbine disk; and a plurality of radial inflow turbine nozzle guide vanes located radially outward of the turbine disk and having an inlet for accepting combustion exhaust and directing the exhaust to the turbine.
Claim 21
Dependent Claim
155 words
A gas turbine engine comprising: a rotor comprising a shaft having a substantially untapered compressor disk on a first end of the shaft with compressor blades defining a centrifugal compressor and a substantially untapered turbine disk on an opposite end of the shaft with turbine blades defining a radial inflow turbine, the rotor further comprising a material characterized by a strength-to-density ratio enabling a rotor speed of at least about 500,000 rotations per minute; an annular, radial out-flow diffuser located radially outward of the compressor disk for receiving compressed air from the compressor; an annular combustor located radially outward of the rotor shaft, having a combustor inlet radially outward of the diffuser, and having an exhaust outlet radially outward of the turbine disk; and a plurality of radial inflow turbine nozzle guide vanes located radially outward of the turbine disk and having an inlet for accepting combustion exhaust and directing the exhaust to the turbine.
Claim 22
Dependent Claim
54 words
The gas turbine engine of claim 14 wherein the compressor and turbine disks each comprise a disk diameter of between about 1 mm and 20 mm and wherein the combustor comprises a combustion chamber having an annular height of between about 2 mm-10 mm and an axial length of between about 0.5 mm-12 mm.
Claim 23
Dependent Claim
34 words
The gas turbine engine of claim 14 wherein the combustor comprises a combustion chamber having dimensions characterized by a ratio of chamber annular height to chamber axial length that is at least about 1.
Claim 24
Dependent Claim
39 words
The gas turbine engine of claim 14 wherein the rotor shaft is journalled for rotation by a radial gas journal bearing having a clearance of between about 2 μm-25 μm between the rotor shaft and an engine housing wall.
Claim 25
Dependent Claim
20 words
The gas turbine engine of claim 17 wherein the radial gas journal bearing has a tangential, circumferentially asymmetric pressurization seal.
Claim 26
Dependent Claim
43 words
The gas turbine engine of claim 14 wherein the compressor disk and the turbine disk are each journalled for rotation by a radial gas journal bearing having a clearance between a radially peripheral edge of the disk and a corresponding engine housing wall.
Claim 27
Dependent Claim
21 words
The gas turbine engine of claim 14 wherein the compressor disk and the turbine disk are located back-to-back on the rotor.
Claim 28
Dependent Claim
62 words
The gas turbine engine of claim 14 wherein the compressor blades comprise a plurality of radial-flow blades together of a common axial height and each of a constant axial height along blade radial extent, and wherein the turbine blades comprise a plurality of radial-flow blades together of a common axial height and each of a constant axial height along blade radial extent.
Claim 29
Dependent Claim
75 words
The gas turbine engine of claim 21 wherein the diffuser comprises a plurality of radial-flow diffuser vanes together of a common axial height with the plurality of compressor blades and each of a constant axial height along vane radial extent, and wherein the turbine guide vanes comprise a plurality of radial-flow vanes together of a common axial height with the plurality of turbine blades and each of a constant axial height along vane radial extent.
Claim 30
Dependent Claim
50 words
The gas turbine engine of claim 14 further comprising a motor having a motor rotor defined by the compressor and having stator electrodes defined by conducting regions located on an engine endwall opposite the compressor disk and interconnected to define a stator excitation configuration of at least two excitation phases.
Claim 31
Dependent Claim
17 words
The gas turbine engine of claim 23 wherein the motor rotor is defined by the compressor blades.
Claim 32
Dependent Claim
61 words
The gas turbine engine of claim 23 wherein the compressor blades comprise a plurality of radial-flow blades together of a common axial height and each of a constant axial height along blade radial extent, the compressor further comprising a blade shroud connected on the axial height of the blades and having an upper conducting layer defining an electric induction motor rotor.
Claim 33
Dependent Claim
50 words
The gas turbine engine of claim 14 further comprising a generator having a generator rotor defined by the compressor and having stator electrodes defined by conducting regions located on an engine endwall opposite the compressor disk and interconnected to define a stator excitation configuration of at least one excitation phase.
Claim 34
Dependent Claim
50 words
The gas turbine engine of claim 14 further comprising a generator having a generator rotor defined by the turbine and having stator electrodes defined by conducting regions located on an engine endwall opposite the turbine disk and interconnected to define a stator excitation configuration of at least one excitation phase.
Claim 35
Dependent Claim
50 words
The gas turbine engine of claim 14 further comprising a motor having a motor rotor defined by the turbine and having stator electrodes defined by conducting regions located on an engine endwall opposite the turbine disk and interconnected to define a stator excitation configuration of at least two excitation phases.
Claim 36
Dependent Claim
17 words
The gas turbine engine of claim 27 wherein the generator rotor is defined by the turbine blades.
Claim 37
Dependent Claim
61 words
The gas turbine engine of claim 27 wherein the turbine blades comprise a plurality of radial-flow blades together of a common axial height and each of a constant axial height along blade radial extent, the turbine further comprising a blade shroud connected on the axial height of the blades and having an upper conducting layer defining an electric induction generator rotor.
Claim 38
Dependent Claim
48 words
The gas turbine engine of claim 14 further comprising: an annular fuel plenum located radially outward of the compressor disk; and an array of fuel injectors connected between the fuel plenum and a location on an engine endwall along internal engine air flow upstream of the combustor inlet.
Claim 39
Dependent Claim
101 words
The gas turbine engine of claim 31 further comprising a fuel tank, a motor connected to the rotor, an auxiliary power source for starting the motor, and control electronics, and wherein the gas turbine engine is housed in an engine package having a air inlet port connected to the compressor, an air exhaust port connected to the turbine, a fuel port connected to the fuel tank, a fuel line connecting the fuel tank to the fuel plenum, an electrical port connected to the control electronics and auxiliary power source, and an isolation wall isolating the fuel tank from other engine components.
Claim 40
Dependent Claim
19 words
The gas turbine engine of claim 32 wherein the engine package comprises a volume less than about 1 liter.
Claim 41
Dependent Claim
26 words
The gas turbine engine of claim 32 wherein the fuel tank comprises a volume sufficient for storing between about 5 ml-5000 ml of liquid engine fuel.
Claim 42
Dependent Claim
15 words
The gas turbine engine of claim 32 wherein the engine package comprises a plastic package.
Claim 43
Dependent Claim
42 words
The gas turbine engine of claim 14 further comprising an annular recuperator connected to receive compressed air from the diffuser and to receive air exhausted from the turbine to heat the compressed air and discharge the heated compressed air to the combuster.
Claim 44
Dependent Claim
40 words
The gas turbine engine of claim 36 wherein the recuperator comprises planar hot air channels connected to receive air exhausted from the turbine and located in alternating fashion with cold air channels connected to receive compressed air from the diffuser.
Claim 45
Dependent Claim
45 words
The gas turbine engine of claim 14 further comprising: a bypass fan located axially forward of the compressor disk and having bypass fan blades; and an axial bypass channel located radially outward of the combustor and providing an exhaust port axially aft of the turbine.
Claim 46
Dependent Claim
72 words
The gas turbine engine of claim 38 wherein the compressor blades comprise a plurality of radial-flow blades together of a common axial height and each of a constant axial height along blade radial extent, the compressor further comprising a blade shroud connected on the axial height of the blades and supporting the bypass fan blades, together of a common axial height and each of a constant axial height along blade radial extent.
Claim 47
Dependent Claim
30 words
The gas turbine engine of claim 14 wherein the rotor, diffuser, combustor, and turbine nozzle guide vanes elements each substantially comprise a structural material common to all of the elements.
Claim 48
Dependent Claim
39 words
The gas turbine engine of claim 14 wherein the rotor, diffuser, combustor, and turbine nozzle guide vane elements each comprise a microfabricated element, and a ratio of engine radial height to engine axial length is at least about 1.
Claim 49
Dependent Claim
160 words
A gas turbine engine comprising: a rotor comprising a shaft having a compressor disk on a first end of the shaft with compressor blades defining a centrifugal compressor and a turbine disk on an opposite end of the shaft with turbine blades defining a radial inflow turbine; an annular, radial out-flow diffuser located radially outward of the compressor disk for receiving compressed air from the compressor; an annular, linerless combustor having a combustion chamber located radially outward of the rotor shaft, having a combustor inlet radially outward of the diffuser, and having an exhaust outlet radially outward of the turbine disk, the combustion chamber having dimensions characterized by a ratio of chamber annular height to chamber axial length that is at least about 1; and a plurality of radial in-flow turbine nozzle guide vanes located radially outward of the turbine disk and having an inlet for accepting combustion exhaust from the combustion chamber and directing the exhaust to the turbine.
Claim 50
Dependent Claim
160 words
A gas turbine engine comprising: a rotor comprising a shaft having a compressor disk on a first end of the shaft with compressor blades defining a centrifugal compressor and a turbine disk on an opposite end of the shaft with turbine blades defining a radial inflow turbine; an annular, radial out-flow diffuser located radially outward of the compressor disk for receiving compressed air from the compressor; an annular, linerless combustor having a combustion chamber located radially outward of the rotor shaft, having a combustor inlet radially outward of the diffuser, and having an exhaust outlet radially outward of the turbine disk, the combustion chamber having dimensions characterized by a ratio of chamber annular height to chamber axial length that is at least about 1; and a plurality of radial in-flow turbine nozzle guide vanes located radially outward of the turbine disk and having an inlet for accepting combustion exhaust from the combustion chamber and directing the exhaust to the turbine.
Claim 51
Dependent Claim
54 words
The gas turbine engine of claim 42 wherein the compressor and turbine disks each comprise a disk diameter of between about 1 mm and 20 mm and wherein the combustor comprises a combustion chamber having an annular height of between about 2 mm-10 mm and an axial length of between about 0.5 mm-12 mm.
Claim 52
Dependent Claim
21 words
The gas turbine engine of claim 42 wherein the compressor disk and the turbine disk are located back-to-back on the rotor.
Claim 53
Dependent Claim
62 words
The gas turbine engine of claim 42 wherein the compressor blades comprise a plurality of radial-flow blades together of a common axial height and each of a constant axial height along blade radial extent, and wherein the turbine blades comprise a plurality of radial-flow blades together of a common axial height and each of a constant axial height along blade radial extent.
Claim 54
Dependent Claim
76 words
The gas turbine engine of claim 42 wherein the diffuser comprises a plurality of radial-flow diffuser vanes together of a common axial height with the plurality of compressor blades and each of a constant axial height along vane radial extent, and wherein the turbine nozzle guide vanes comprise a plurality of radial-flow vanes together of a common axial height with the plurality of turbine blades and each of a constant axial height along vane radial extent.
Claim 55
Dependent Claim
48 words
The gas turbine engine of claim 42 further comprising: an annular fuel plenum located radially outward of the compressor disk; and an array of fuel injectors connected between the fuel plenum and a location on an engine endwall along internal engine air flow upstream of the combustor inlet.
Claim 56
Dependent Claim
101 words
The gas turbine engine of claim 47 further comprising a fuel tank, a motor connected to the rotor, an auxiliary power source for starting the motor, and control electronics, and wherein the gas turbine engine is housed in an engine package having a air inlet port connected to the compressor, an air exhaust port connected to the turbine, a fuel port connected to the fuel tank, a fuel line connecting the fuel tank to the fuel plenum, an electrical port connected to the control electronics and auxiliary power source, and an isolation wall isolating the fuel tank from other engine components.
Claim 57
Dependent Claim
31 words
The gas turbine engine of claim 42 wherein the rotor, diffuser, combustion chamber, and turbine nozzle guide vane elements each substantially comprise a structural material common to all of the elements.
Claim 58
Dependent Claim
40 words
The gas turbine engine of claim 42 wherein the rotor, diffuser, combustion chamber, and turbine nozzle guide vane elements each comprise a microfabricated element, and a ratio of engine radial height to engine axial length is at least about 1.
Claim 59
Dependent Claim
123 words
A gas turbine engine comprising: a compressor disk having radial-flow compressor blades defining a centrifugal compressor; a turbine disk located in a plane coincident with the compressor disk and having radial-flow turbine blades defining a radial inflow turbine; an annular, radial out-flow diffuser located radially outward of the compressor disk for receiving compressed air from the compressor; a combustor having a combustion chamber with a combustor inlet in communication with the diffuser for receiving compressed air from the diffuser and an exhaust vent in the plane of the turbine disk; and a plurality of radial inflow turbine nozzle guide vanes located radially outward of the turbine disk and having an inlet for accepting combustion exhaust and directing the exhaust to the turbine disk.
Claim 60
Dependent Claim
123 words
A gas turbine engine comprising: a compressor disk having radial-flow compressor blades defining a centrifugal compressor; a turbine disk located in a plane coincident with the compressor disk and having radial-flow turbine blades defining a radial inflow turbine; an annular, radial out-flow diffuser located radially outward of the compressor disk for receiving compressed air from the compressor; a combustor having a combustion chamber with a combustor inlet in communication with the diffuser for receiving compressed air from the diffuser and an exhaust vent in the plane of the turbine disk; and a plurality of radial inflow turbine nozzle guide vanes located radially outward of the turbine disk and having an inlet for accepting combustion exhaust and directing the exhaust to the turbine disk.
Claim 61
Dependent Claim
21 words
The gas turbine engine of claim 51 wherein the gas turbine engine has a thickness of less than about 1 centimeter.
Claim 62
Dependent Claim
30 words
The gas turbine engine of claim 51 further comprising a fuel manifold located adjacent to the diffuser and connected to the diffuser by a row of spaced apart fuel injectors.
Claim 63
Dependent Claim
37 words
The gas turbine engine of claim 51 further comprising forward and aft cooling channels each located adjacent to a corresponding forward and aft combustion chamber wall and connected between the diffuser exhaust vent and the combustor inlet.
Claim 64
Dependent Claim
58 words
The gas turbine engine of claim 51 wherein the diffuser comprises a plurality of diffuser vanes, and wherein the compressor blades, the turbine blades, the diffuser vanes, and the turbine nozzle guide vanes comprise radial-flow blades and vanes together of a common axial height and each of a constant axial height along corresponding blade and vane radial extent.
Claim 65
Dependent Claim
50 words
The gas turbine engine of claim 51 further comprising a motor having a motor rotor defined by the compressor disk and stator electrodes defined by conducting regions located on an engine endwall opposite the compressor disk and interconnected to define a stator excitation configuration of at least two excitation phases.
Claim 66
Dependent Claim
51 words
The gas turbine engine of claim 51 further comprising a generator having a generator rotor defined by the turbine disk and having stator electrodes defined by conducting regions located on an engine endwall opposite the turbine disk and interconnected to define a stator excitation configuration of at least one excitation phase.
Claim 67
Dependent Claim
214 words
A combustion power generator comprising: a first pump disk having pump blades defining a rotary fuel pump; a second pump disk located in a plane coincident with the first pump disk and having pump blades defining a rotary oxidizer pump; a turbine disk located in a plane coincident with the first and second pump disks and having turbine blades defining a radial inflow turbine; a first annular, radial out-flow diffuser located radially outward of the first pump disk for receiving fuel from the fuel pump; a second annular, radial out-flow diffuser located radially outward of the second pump disk for receiving oxidizer from the oxidizer pump; a combustor comprising a combustion chamber with a combustor inlet in communication with the first and second diffusers for receiving fuel and oxidizer, and an exhaust vent in the plane of the turbine disk; a plurality of radial inflow turbine nozzle guide vanes located radially outward of the turbine disk and having an inlet for accepting combustion exhaust and directing the exhaust to the turbine disk; and a generator having a generator rotor defined by the turbine and having stator electrodes defined by conducting regions located on a generator endwall opposite the turbine disk and interconnected to define a stator excitation configuration of at least one excitation phase.
Claim 68
Dependent Claim
214 words
A combustion power generator comprising: a first pump disk having pump blades defining a rotary fuel pump; a second pump disk located in a plane coincident with the first pump disk and having pump blades defining a rotary oxidizer pump; a turbine disk located in a plane coincident with the first and second pump disks and having turbine blades defining a radial inflow turbine; a first annular, radial out-flow diffuser located radially outward of the first pump disk for receiving fuel from the fuel pump; a second annular, radial out-flow diffuser located radially outward of the second pump disk for receiving oxidizer from the oxidizer pump; a combustor comprising a combustion chamber with a combustor inlet in communication with the first and second diffusers for receiving fuel and oxidizer, and an exhaust vent in the plane of the turbine disk; a plurality of radial inflow turbine nozzle guide vanes located radially outward of the turbine disk and having an inlet for accepting combustion exhaust and directing the exhaust to the turbine disk; and a generator having a generator rotor defined by the turbine and having stator electrodes defined by conducting regions located on a generator endwall opposite the turbine disk and interconnected to define a stator excitation configuration of at least one excitation phase.
Claim 69
Dependent Claim
159 words
A combustion power generator comprising: a pump disk having pump blades defining a rotary fuel pump; a turbine disk located in a plane coincident with the pump disk and having turbine blades defining a radial inflow turbine; an annular, radial out-flow diffuser located radially outward of the pump disk for receiving fuel from the fuel pump; a combustor comprising a combustion chamber with a combustor inlet in communication with the diffuser for receiving fuel, and an exhaust vent in the plane of the turbine disk; a plurality of radial inflow turbine nozzle guide vanes located radially outward of the turbine disk and having an inlet for accepting combustion exhaust and directing the exhaust to the turbine disk; and a generator having a generator rotor defined by the turbine and having stator electrodes defined by conducting regions located on a generator endwall opposite the turbine disk and interconnected to define a stator excitation configuration of at least one excitation phase.
Claim 70
Dependent Claim
159 words
A combustion power generator comprising: a pump disk having pump blades defining a rotary fuel pump; a turbine disk located in a plane coincident with the pump disk and having turbine blades defining a radial inflow turbine; an annular, radial out-flow diffuser located radially outward of the pump disk for receiving fuel from the fuel pump; a combustor comprising a combustion chamber with a combustor inlet in communication with the diffuser for receiving fuel, and an exhaust vent in the plane of the turbine disk; a plurality of radial inflow turbine nozzle guide vanes located radially outward of the turbine disk and having an inlet for accepting combustion exhaust and directing the exhaust to the turbine disk; and a generator having a generator rotor defined by the turbine and having stator electrodes defined by conducting regions located on a generator endwall opposite the turbine disk and interconnected to define a stator excitation configuration of at least one excitation phase.
Claim 71
Dependent Claim
20 words
The combustion power generator of claim 59 wherein the power generator has a thickness of less than about 1 centimeter.
Claim 72
Dependent Claim
59 words
The combustion power generator of claim 59 wherein the diffuser comprises a plurality of diffuser vanes, and wherein the fuel pump blades, the turbine blades, the diffuser vanes, and the turbine nozzle guide vanes comprise radial-flow blades and vanes together of a common axial height and each of a constant axial height along corresponding blade and vane radial extent.
Claim 73
Dependent Claim
38 words
The combustion power generator of claim 59 further comprising: a fuel pump motor having a motor rotor defined by the fuel pump and stator electrodes defined by conducting regions located on an endwall opposite the fuel pump disk.
Claim 74
Dependent Claim
33 words
The combustion power generator of claim 59 wherein the fuel pump, diffuser, combustion chamber, turbine nozzle guide vanes, and turbine elements each substantially comprise a structural material common to all of the elements.
Claim 75
Dependent Claim
41 words
The gas turbine engine of claim 59 wherein the fuel pump, diffuser, combustion chamber, turbine guide vanes, and turbine elements each comprise a microfabricated element, and a ratio of engine radial height to engine axial length is at least about 1.
Claim 76
Dependent Claim
62 words
The gas turbine engine of claim 21 wherein the diffuser comprises a plurality of radial-flow diffuser vanes together of a common axial height that is distinct from axial height of the compressor blades, and wherein the turbine nozzle guide vanes comprise a plurality of radial-flow vanes together of a common axial height that is distinct from axial height of the turbine blades.
Claim 77
Dependent Claim
62 words
The gas turbine engine of claim 42 wherein the diffuser comprises a plurality of radial-flow diffuser vanes together of a common axial height that is distinct from axial height of the compressor blades, and wherein the turbine nozzle guide vanes comprise a plurality of radial-flow vanes together of a common axial height that is distinct from axial height of the turbine blades.
Claim 78
Dependent Claim
116 words
A gas turbine engine comprising: a silicon compressor having an engine inlet port and a rotatable compressor disk for compressing inlet air; a silicon diffuser located to receive compressed air from the compressor and produce a corresponding rise in static air pressure; a silicon carbide combustor comprising a combustion chamber located to receive the compressed air from the diffuser through a combustor inlet to combust the compressed air with a fuel; a plurality of silicon carbide turbine nozzle guide vanes located to receive combusted air exhausted from the combustor; and a silicon carbide turbine having a rotatable turbine disk located to receive combusted air from the turbine nozzle guide vanes, and having an engine exhaust port.
Claim 79
Dependent Claim
116 words
A gas turbine engine comprising: a silicon compressor having an engine inlet port and a rotatable compressor disk for compressing inlet air; a silicon diffuser located to receive compressed air from the compressor and produce a corresponding rise in static air pressure; a silicon carbide combustor comprising a combustion chamber located to receive the compressed air from the diffuser through a combustor inlet to combust the compressed air with a fuel; a plurality of silicon carbide turbine nozzle guide vanes located to receive combusted air exhausted from the combustor; and a silicon carbide turbine having a rotatable turbine disk located to receive combusted air from the turbine nozzle guide vanes, and having an engine exhaust port.
Claim 80
Dependent Claim
180 words
A gas turbine engine comprising: a rotor comprising a shaft having a compressor disk, of between about 1 mm and about 10 mm in diameter, on a first end of the shaft with compressor blades defining a centrifugal compressor, and a turbine disk, of between about 1 mm and about 10 mm in diameter, on an opposite end of the shaft with turbine blades defining a radial inflow turbine; an annular, radial out-flow diffuser located radially outward of the compressor disk for receiving compressed air from the compressor; an annular combustor located radially outward of the rotor shaft, having a combustor inlet radially outward of the diffuser, having an exhaust outlet radially outward of the turbine disk and having a combustion chamber with an annular height of between about 2 mm and about 20 mm and an axial length of between about 0.5 mm and about 12 mm; and a plurality of radial inflow turbine nozzle guide vanes located radially outward of the turbine disk and having an inlet for accepting combustion exhaust and directing the exhaust to the turbine.
Claim 81
Dependent Claim
180 words
A gas turbine engine comprising: a rotor comprising a shaft having a compressor disk, of between about 1 mm and about 10 mm in diameter, on a first end of the shaft with compressor blades defining a centrifugal compressor, and a turbine disk, of between about 1 mm and about 10 mm in diameter, on an opposite end of the shaft with turbine blades defining a radial inflow turbine; an annular, radial out-flow diffuser located radially outward of the compressor disk for receiving compressed air from the compressor; an annular combustor located radially outward of the rotor shaft, having a combustor inlet radially outward of the diffuser, having an exhaust outlet radially outward of the turbine disk and having a combustion chamber with an annular height of between about 2 mm and about 20 mm and an axial length of between about 0.5 mm and about 12 mm; and a plurality of radial inflow turbine nozzle guide vanes located radially outward of the turbine disk and having an inlet for accepting combustion exhaust and directing the exhaust to the turbine.
Claim 82
Dependent Claim
16 words
The gas turbine engine of claim 4 wherein the silicon elements are coated with silicon carbide.
Claim 83
Dependent Claim
16 words
The gas turbine engine of claim 4 wherein the silicon elements are coated with silicon nitride.
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USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 2002-08-02 | 2003-02-01 | 2003-08-03 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 2006-08-02 | 2007-02-01 | 2007-08-03 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2010-08-02 | 2011-02-01 | 2011-08-03 | $7700.00 | Window Closed / Lapsed |