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US5372005A
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US
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Method and apparatus for power generation
Assignee: Dresser Rand Co
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Filing: 1992-09-14
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Granted: 1994-12-13
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Expires: 2012-09-14
Abstract
Abstract Thrust modules are provided at the distal ends of a low aerodynamic drag rotor. The rotor is affixed at a central hub to a shaft, and rotates about an axis defined by the shaft. In the preferred embodiment the thrust modules are ramjet engines, and the ramjet inlet captures and compresses an impinging inlet air stream. The compressed air stream thus provides oxygen for mixing with a fuel which is supplied to the ramjet thrust modules from a convenient fuel source such as natural gas. The fuel is oxidized in the thrust modules to produce combustion gases. The gases expand, and the exhaust flow creates thrust which is substantially tangential to the circumference defined by the distal end of the rotor. The gases expand to motivate the ramjet engine to rotate about the shaft at supersonic thrust module velocities, producing shaft energy.
Inventors
- 👤 Shawn P. Lawler
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-01 02:11
CPC Classifications
F; F02; F02K; F02K7/00; F02K7/005; F02C; F02C3/00; F02C3/14; F02C3/16; F02C3/165; Y; Y02; Y02E; Y02E20/00; Y02E20/16; Y02T; Y02T50/00; Y02T50/60
Claims Analysis
Total Claims: 31
Claim 1
Independent Claim
149 words
A method for generating power, comprising: (a) providing a housing means, (b) providing an output means, said output means further comprising shaft portions, said shaft portions rotatably secured about an axis of rotation by said housing means; (c) providing a rotor means, said rotor means secured to said output means; (d) providing a ramjet means, said ramjet means secured to said rotor means, said ramjet means operating at a velocity of at least Mach 1; (e) providing a fuel supply means; (f) providing a fuel supply conduit to contain fuel while said fuel travels from said fuel supply means to said ramjet means; (e) wherein said ramjet means oxidizes the fuel supplied thereto to generate combustion gases which produce thrust from said ramjet means so as to rotate said ramjet means, rotor means, and output means, to thereby enable said output means to provide power output from said apparatus.
Claim 2
Independent Claim
149 words
A method for generating power, comprising: (a) providing a housing means, (b) providing an output means, said output means further comprising shaft portions, said shaft portions rotatably secured about an axis of rotation by said housing means; (c) providing a rotor means, said rotor means secured to said output means; (d) providing a ramjet means, said ramjet means secured to said rotor means, said ramjet means operating at a velocity of at least Mach 1; (e) providing a fuel supply means; (f) providing a fuel supply conduit to contain fuel while said fuel travels from said fuel supply means to said ramjet means; (e) wherein said ramjet means oxidizes the fuel supplied thereto to generate combustion gases which produce thrust from said ramjet means so as to rotate said ramjet means, rotor means, and output means, to thereby enable said output means to provide power output from said apparatus.
Claim 3
Independent Claim
18 words
The method of claim one wherein said ramjet means operates at a speed of at least Mach 3.0.
Claim 4
Independent Claim
19 words
The method of claim one wherein said ramjet means operates at a speed between Mach 3.0 and mach 4.5.
Claim 5
Independent Claim
14 words
The method of claim one wherein said ramjet means operates at approximately mach 3.5.
Claim 6
Independent Claim
35 words
The method of claim one, further comprising providing an electrical generator, said generator operatively connected to said output means, so that rotation of said output means will energize said generator, to thereby generate electrical power.
Claim 7
Independent Claim
103 words
A method of generating power, comprising: (a) supplying an oxidizable fuel to one or more ramjets (b) oxidizing said fuel in said one or more ramjets to (i) generate combustion gases which escape therefrom, and to (ii) generate a motive force by thrust reaction of said one or more ramjets to said escaping combustion gases, (c) propelling said one or more ramjets at a velocity in excess of Mach 1.0 through a fluid stream by way of said motive force, and (d) turning an output shaft operatively connected to said one or more ramjets; (e) whereby power is provided at said output shaft.
Claim 8
Independent Claim
103 words
A method of generating power, comprising: (a) supplying an oxidizable fuel to one or more ramjets (b) oxidizing said fuel in said one or more ramjets to (i) generate combustion gases which escape therefrom, and to (ii) generate a motive force by thrust reaction of said one or more ramjets to said escaping combustion gases, (c) propelling said one or more ramjets at a velocity in excess of Mach 1.0 through a fluid stream by way of said motive force, and (d) turning an output shaft operatively connected to said one or more ramjets; (e) whereby power is provided at said output shaft.
Claim 9
Dependent Claim
21 words
The method as recited in claim 6 wherein the velocity of said one or more ramjets is at least Mach 3.0.
Claim 10
Dependent Claim
23 words
The method as recited in claim 6 wherein the velocity of said one or more ramjets is between Mach 3.0 and Mach 4.5.
Claim 11
Dependent Claim
26 words
The method as recited in claim 8, further comprising the step of substantially cancelling supersonic shock waves in said fluid stream to thereby minimize aerodynamic drag.
Claim 12
Dependent Claim
73 words
The method as recited in claim 9, wherein said step of substantially cancelling supersonic shock waves in said fluid stream includes directing said fluid stream through a matched pair of substantially triangular bi-plane rotor arms, and wherein said arms are configured in opposing fashion to provide a minimum fluid passage gap therebetween, so that the shock waves produced by each of the arms substantially cancels the shock wave produced by said opposing arm.
Claim 13
Dependent Claim
36 words
The method as recited in claim 8, further comprising the step of providing flow of said fluid stream at a rate sufficient to avoid wake turbulence during the passage of the next one or more ramjets.
Claim 14
Dependent Claim
57 words
The method as recited in claim of claim 11, wherein the step of providing fluid flow further comprises supplying external air to a vent structure, to enable said one or more ramjets to engage fresh vent air substantially free of such turbulence during passage of the next one or more ramjets through a given vent passage location.
Claim 15
Dependent Claim
30 words
The method as recited in claim 12, wherein the step of supplying external air to a vent structure further comprises directing the external air generally upward through a vent structure.
Claim 16
Dependent Claim
21 words
The method as recited in claim 6 wherein the operational velocity of said one or more ramjets is approximately Mach 3.5.
Claim 17
Dependent Claim
19 words
The method as recited in claim 6, wherein said fuel is selected from the group comprising gaseous hydrocarbon fuels.
Claim 18
Dependent Claim
14 words
The method as recited in claim 15, wherein said fuel is essentially natural gas.
Claim 19
Dependent Claim
28 words
The method as recited in claim 6, wherein the step of supplying fuel includes the step of supplying said fuel axially through a bore in said output shaft.
Claim 20
Dependent Claim
17 words
The method as recited in claim 6, wherein said method further includes the step of generating electricity.
Claim 21
Dependent Claim
23 words
The method as recited in claim 18, wherein the step of generating electricity comprises operatively connecting an electrical generator to said output shaft.
Claim 22
Dependent Claim
73 words
The method as recited in claim 6, further comprising the step of passing said combustion gases through a reaction turbine, wherein said reaction turbine is situated in an operative position wherein said combustion gases from said ramjet one or more ramjets are directed at said reaction turbine, so that said reaction turbine is rotated by the passage of said combustion gases through said reaction turbine, to provide power output from said reaction turbine.
Claim 23
Dependent Claim
22 words
The method as recited in claim 6, wherein said method further includes the step of recovering thermal energy from said combustion gases.
Claim 24
Dependent Claim
28 words
The method as recited in claim 21, wherein said thermal energy recovery step comprises transfer of said thermal energy from said combustion gases to a secondary working fluid.
Claim 25
Dependent Claim
66 words
The method as recited in claim 22, further comprising the step of passing said combustion gases through a reaction turbine, wherein said reaction turbine is situated in an operative position wherein said combustion gases are directed to said reaction turbine, so that said reaction turbine is rotated by the passage of said combustion gases through said reaction turbine, to provide power output from said reaction turbine.
Claim 26
Dependent Claim
41 words
The method as recited in claim 23, wherein the step of passing combustion gases through a reaction turbine is preceded by the step of passing said combustion gases radially outward from said heat recovery section and thence into said reaction turbine.
Claim 27
Dependent Claim
23 words
The method as recited in claim 22, wherein said secondary working fluid is water, and wherein steam is produced by heating said water.
Claim 28
Dependent Claim
28 words
The method as recited in claim 25, wherein said thermal energy recovery step comprises indirect heating of said water by said combustion gases in a heat recovery section.
Claim 29
Dependent Claim
77 words
The method as recited in claim 26, further comprising the step of minimizing pressure drop of said combustion gases during said thermal energy recovery step, wherein said thermal energy recovery step is accomplished (i) by directing said combustion gases in a heat transfer relationship past generally airfoil shaped aerodynamically low pressure drop heat transfer structures in said heat recovery section, and (ii) by passing said secondary working fluid through an interior portion of said heat transfer structures.
Claim 30
Dependent Claim
38 words
The method as recited claim 25, further comprising the step of directing said steam to a steam turbine, to generate power by rotation of said steam turbine by said steam, to produce shaft work from said steam turbine.
Claim 31
Dependent Claim
22 words
The method as recited in claim 28, further comprising the step of generating electricity from said shaft work of said steam turbine.
References Cited (Backward Citations)
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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) | 1997-12-12 | 1998-06-13 | 1998-12-13 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 2001-12-12 | 2002-06-13 | 2002-12-13 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2005-12-12 | 2006-06-13 | 2006-12-13 | $7700.00 | Window Closed / Lapsed |