US3810360A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Gas generator with selectively connectible turbine system
Assignee: MTU Aero Engines AG
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Filing: 1972-10-20
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Granted: 1974-05-14
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Expires: 1992-10-20
Abstract
Abstract An engine arrangement for use with a vertical/short take-off and landing airplane having a gas generator supplying exhaust gases selectively to a turbine system and to a thrust nozzle. The turbine system is connectible to auxiliary lift devices, such as a lift rotor, for effecting vertical lift operations while the thrust nozzle is designed for normal cruising operations. The flow of exhaust gases to the turbine system and the thrust nozzle is controlled such that the total cross-sectional area, with respect to the exhaust gas flow, of both the turbine system and the thrust nozzle is maintained constant for all operations. Sliding members are arranged at the respective critical crosssections in the inlets to the turbine system and thrust nozzle for blocking the exhaust gas flow. These sliding members are interconnected to one another such that opening of one causes a corresponding similar closing of the other.
Inventors
- 👤 H Leibach
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-28 10:57
CPC Classifications
F; F02; F02K; F02K3/00; F02K3/02; F02K3/04; F02K3/075; F02K3/025
Claims Analysis
Total Claims: 35
Claim 1
Independent Claim
206 words
An engine arrangement comprising: gas generator means for supplying exhuast gases, a turbine system arranged downstream of said gas generator means, said turbine system having a first inlet for accepting said exhaust gases to drive said turbine system, said first inlet having a first critical cross-section corresponding to optimum driving of said turbine system by said exhaust gases, a thrust nozzle arranged downstream of said gas generator means, said thrust nozzle having a second inlet for accepting said exhaust gases, said second inlet having a second critical cross-section corresponding to optimum operation of said thrust nozzle by said exhaust gases, first inlet blocking means for selectively varying the inlet opening at said first critical cross-section, second inlet blocking means for selectively varying the inlet opening at said second critical cross-section, and control means interconnecting said first and second inlet blocking means such that opening of said first critical crosssection results in simultaneous closing of said second critical cross-section and a closing of said first critical crosssection results in simultaneous opening of said second critical cross-section, wherein said first and second critical cross sections are annular shaped, and wherein said first and second inlet blocking means are constructed as respective rotationally symmetrical first and second slide members.
Claim 2
Dependent Claim
206 words
An engine arrangement comprising: gas generator means for supplying exhuast gases, a turbine system arranged downstream of said gas generator means, said turbine system having a first inlet for accepting said exhaust gases to drive said turbine system, said first inlet having a first critical cross-section corresponding to optimum driving of said turbine system by said exhaust gases, a thrust nozzle arranged downstream of said gas generator means, said thrust nozzle having a second inlet for accepting said exhaust gases, said second inlet having a second critical cross-section corresponding to optimum operation of said thrust nozzle by said exhaust gases, first inlet blocking means for selectively varying the inlet opening at said first critical cross-section, second inlet blocking means for selectively varying the inlet opening at said second critical cross-section, and control means interconnecting said first and second inlet blocking means such that opening of said first critical crosssection results in simultaneous closing of said second critical cross-section and a closing of said first critical crosssection results in simultaneous opening of said second critical cross-section, wherein said first and second critical cross sections are annular shaped, and wherein said first and second inlet blocking means are constructed as respective rotationally symmetrical first and second slide members.
Claim 3
Dependent Claim
171 words
An arrangement according to claim 1, wherein said first inlet blocking means includes means for varying the opening at said first critical cross section from an extreme open position corresponding to optimum operation of said turbine system utilizing all of said exhaust gases to an extreme closed position corresponding to complete shutdown of said turbine system utilizing none of said exhaust gases, wherein said second inlet blocking means includes means for varying the opening at said second critical cross section from an extreme open position corresponding to optimum operation of said thrust nozzle utilizing all of said exhaust gases to an extreme closed position corresponding to a complete shutdown of said thrust nozzle utilizing none of said exhaust gases, and wherein said control means includes means for placing said first inlet blocking means in said closed position when said second inlet blocking means is in said open position and for placing said first inlet blocking means in said open position when said second inlet blocking means is in said closed position.
Claim 4
Dependent Claim
22 words
An arrangement according to claim 1, wherein said first critical cross section has the same size as said second critical cross section.
Claim 5
Dependent Claim
22 words
An arrangement according to claim 2, wherein said first critical cross section has the same size as said second critical cross section.
Claim 6
Dependent Claim
73 words
An arrangement according to claim 4, wherein said control means includes a common control device for moving said slide members in such a manner that closing movement of one of said slide members is accompanied by a similar opening movement of the other of said slide members, whereby the total cross sectional area at said first and second cross sections remains constant for all operating conditions of the turbine system and thrust nozzle.
Claim 7
Dependent Claim
19 words
An arrangement according to claim 5, wherein said common control device includes pneumatic means for moving said slide members.
Claim 8
Dependent Claim
35 words
An arrangement according to claim 5, wherein said second critical cross section is formed between a terminal edge of said second slide member and a terminal edge of an annular jacket surrounding the turbine system.
Claim 9
Dependent Claim
37 words
An arrangement according to claim 7, wherein said first critical cross section is formed between a divergent wall section of an inner central element of the turbine system and a terminal edge of said first slide member.
Claim 10
Dependent Claim
32 words
An arrangement according to claim 8, wherein said first critical cross section is formed between an outer wall section of said first inlet and a terminal section of said first slide member.
Claim 11
Dependent Claim
41 words
An arrangement according to claim 9, wherein said first slide member is shaped in the form of a central element provided with a curved wall section for aerodynamically guiding said exhaust gases to one of said turbine system and thrust nozzle.
Claim 12
Dependent Claim
45 words
An arrangement according to claim 10, wherein said gas generator means and said thrust nozzle are disposed in a common plane, and wherein said turbine system and said first inlet blocking means are disposed in a plane spatially offset with respect to said common plane.
Claim 13
Dependent Claim
57 words
An arrangement according to claim 10, wherein said gas generator means includes a turbine and compressor unit mounted for rotation on a gas generator shaft, wherein said turbine system includes a turbine wheel mounted for rotation on a turbine system shaft, and wherein said turbine system shaft and said gas generator shaft extend along a common axis.
Claim 14
Dependent Claim
17 words
An arrangement according to claim 12, wherein said thrust nozzle is symmetrically arranged about said common axis.
Claim 15
Dependent Claim
26 words
An arrangement according to claim 10, wherein said thrust nozzle is symmetrically arranged about an axis extending in the longitudinal direction of said gas generator shaft.
Claim 16
Dependent Claim
32 words
An arrangement according to claim 5, wherein said first critical cross section is formed between an outer wall section of said first inlet and a terminal section of said first slide member.
Claim 17
Dependent Claim
45 words
An arrangement according to claim 5, wherein said gas generator means and said thrust nozzle are disposed in a common plane, and wherein said turbine system and said first inlet blocking means are disposed in a plane spatially offset with respect to said common plane.
Claim 18
Dependent Claim
37 words
An arrangement according to claim 5, wherein said first critical cross section is formed between a divergent wall section of an inner central element of the turbine system and a terminal edge of said first slide member.
Claim 19
Dependent Claim
35 words
An arrangement according to claim 4, wherein said second critical cross section is formed between a terminal edge of said second slide member and a terminal edge of an annular jacket surrounding the turbine system.
Claim 20
Dependent Claim
37 words
An arrangement according to claim 4, wherein said first critical cross section is formed Between a divergent wall section of an inner central element of the turbine system and a terminal edge of said first slide member.
Claim 21
Dependent Claim
32 words
An arrangement according to claim 4, wherein said first critical cross section is formed between an outer wall section of said first inlet and a terminal section of said first slide member.
Claim 22
Dependent Claim
41 words
An arrangement according to claim 20, wherein said first slide member is shaped in the form of a central element provided with a curved wall section for aerodynamically guiding said exhaust gases to one of said turbine system and thrust nozzle.
Claim 23
Dependent Claim
45 words
An arrangement according to claim 4, wherein said gas generator means and said thrust nozzle are disposed in a common plane, and wherein said turbine system and said first inlet blocking means are disposed in a plane spatially offset with respect to said common plane.
Claim 24
Dependent Claim
57 words
An arrangement according to claim 4, wherein said gas generator means includes a turbine and compressor unit mounted for rotation on a gas generator shaft, wherein said turbine system includes a turbine wheel mounted for rotation on a turbine system shaft, and wherein said turbine system shaft and said gas generator shaft extend along a common axis.
Claim 25
Dependent Claim
17 words
An arrangement according to claim 23, wherein said thrust nozzle is symmetrically arranged about said common axis.
Claim 26
Dependent Claim
23 words
An arrangement according to claim 23, wherein said slide members are constrained to move only in a direction parallel to said common axis.
Claim 27
Dependent Claim
57 words
An arrangement according to claim 4, wherein said gas generator means includes a turbine and compressor unit mounted for rotation on a gas generator shaft, wherein said turbine system includes a turbine wheel mounted for rotation on a turbine system shaft, and wherein said turbine system shaft is angularly disposed with respect to said gas generator shaft.
Claim 28
Dependent Claim
30 words
An arrangement according to claim 26, wherein said control means includes a common drive motor drivingly connected to said first and second slide members by way of shafts and spindles.
Claim 29
Dependent Claim
45 words
An arrangement according to claim 26, wherein said first slide member is constrained to move only in a direction parallel to said turbine system shaft, and wherein said second slide member is constrained to move only in a direction parallel to said gas generator shaft.
Claim 30
Dependent Claim
30 words
An arrangement according to claim 4, wherein said control means includes a common drive motor drivingly connected to said first and second slide members by way of shafts and spindles.
Claim 31
Dependent Claim
38 words
An arrangement according to claim 29, wherein said turbine system includes means for driving a lift rotor or lifting jet of an airplane, and wherein said thrust nozzle is operatively arranged for providing cruising thrust to said airplane.
Claim 32
Dependent Claim
38 words
An arrangement according to claim 4, wherein said turbine system includes means for driving a lift rotor or lifting jet of an airplane, and wherein said thrust nozzle is operatively arranged for providing cruising thrust to said airplane.
Claim 33
Dependent Claim
35 words
An arrangement according to claim 3, wherein said second critical cross section is formed between a terminal edge of said second slide member and a terminal edge of an annular jacket surrounding the turbine system.
Claim 34
Dependent Claim
37 words
An arrangement according to claim 3, wherein said first critical cross section is formed between a divergent wall section of an inner central element of the turbine system and a terminal edge of said first slide member.
Claim 35
Dependent Claim
38 words
An arrangement according to claim 1, wherein said turbine system includes means for driving a lift rotor or lifting jet of an airplane, and wherein said thrust nozzle is operatively arranged for providing cruising thrust to said airplane.
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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) | 1977-05-13 | 1977-11-12 | 1978-05-14 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1981-05-13 | 1981-11-12 | 1982-05-14 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1985-05-13 | 1985-11-12 | 1986-05-14 | $7700.00 | Window Closed / Lapsed |