Patent US4815282A successfully refreshed from Google Patents.
US4815282A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Turbocharged compund cycle ducted fan engine system
Assignee: Teledyne Technologies Inc
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Filing: 1987-02-24
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Granted: 1989-03-28
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Expires: 2007-02-24
Abstract
Abstract A turbocharged, compounded cycle ducted fan engine system includes a conventional internal combustion engine drivingly connected to a fan enclosed in a duct. The fan provides propulsive thrust by accelerating air through the duct and out an exhaust nozzle. A turbocharger is disposed in the duct and out an exhaust nozzle. A turbocharger is disposed in the duct and receives a portion of the air compressed by the fan. The turbocharger compressor further pressurizes the air and directs it to the internal combustion engine where it is burned and exits as exhaust gas to drive the turbine. A power turbine also driven by exhaust gas is also drivingly connected through the engine to the fan to provide additional power. The size and weight of the turbocharger are reduced since the compressor's work is partially achieved by the compression effect of the fan. The total propulsive thrust includes the fan generated thrust which bypasses the turbocharger and the thrust of exhaust gases exiting the turbine.
Inventors
- 👤 Ronald Wilkinson
- 👤 Ralph Benway
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-29 10:16
CPC Classifications
F; F02; F02B; F02B37/00; F02B37/001; F02B37/005; F02B37/04; F02B37/10; F02B37/105; F02B39/00; F02B39/02; F02B39/12; F02B41/00; F02B41/02; F02B41/06; F02C; F02C6/00; F02C6/04; F02C6/10; F02C6/12; F02K; F02K5/00; F02K5/02; Y; Y02; Y02T; Y02T10/00; Y02T10/10; Y02T10/12; Y02T50/00; Y02T50/60
Claims Analysis
Total Claims: 15
Claim 1
Independent Claim
188 words
A propulsion engine system for aircraft comprising: an internal combustion engine including a rotatable drive shaft, an air inlet and an exhaust outlet; a fan for generating thrust, said fan being rotatably mounted in a duct and drivingly connected to said drive shaft; a power turbine shaft, a power turbine rotatable about said power turbine shaft, a power turbine inlet and a power turbine outlet, wherein said power turbine inlet is connected to said exhaust outlet and wherein said power turbine is selectively, drivingly connected to said drive shaft; and a turbocharger including a turbine having an inlet and an outlet and a compressor having an inlet and an outlet, wherein said turbine is arranged for rotation with said compressor, and said turbine inlet is connected to said exhaust outlet and said compressor outlet is connected to said air inlet of said combustion engine; wherein said compressor inlet is disposed in said duct downstream from said fan to receive at least a portion of the air thrust from said fan, said power turbine is disposed coaxial with said turbocharger, and said power turbine rotates independently of said turbine.
Claim 2
Dependent Claim
188 words
A propulsion engine system for aircraft comprising: an internal combustion engine including a rotatable drive shaft, an air inlet and an exhaust outlet; a fan for generating thrust, said fan being rotatably mounted in a duct and drivingly connected to said drive shaft; a power turbine shaft, a power turbine rotatable about said power turbine shaft, a power turbine inlet and a power turbine outlet, wherein said power turbine inlet is connected to said exhaust outlet and wherein said power turbine is selectively, drivingly connected to said drive shaft; and a turbocharger including a turbine having an inlet and an outlet and a compressor having an inlet and an outlet, wherein said turbine is arranged for rotation with said compressor, and said turbine inlet is connected to said exhaust outlet and said compressor outlet is connected to said air inlet of said combustion engine; wherein said compressor inlet is disposed in said duct downstream from said fan to receive at least a portion of the air thrust from said fan, said power turbine is disposed coaxial with said turbocharger, and said power turbine rotates independently of said turbine.
Claim 3
Dependent Claim
26 words
The invention as defined in claim 1, wherein said means for selectively, drivingly connecting comprises reduction gearing between said power turbine shaft and said drive shaft.
Claim 4
Dependent Claim
18 words
The invention as defined in claim 1 wherein said power turbine outlet is connected to said turbine inlet.
Claim 5
Dependent Claim
39 words
The invention as defined in claim 3 and comprising a first waste gate selectively operable to allow exhaust to bypass said power turbine, and a second waste gate selectively operable to allow exhaust gas to bypass said turbocharger turbine.
Claim 6
Dependent Claim
18 words
The invention as defined in claim 1 wherein said internal combustion engine is disposed closely adjacent said turbocharger.
Claim 7
Dependent Claim
24 words
The invention as defined in claim 1 wherein said exhaust outlet and said turbine inlet and intermediate connections are insulated to minimize energy loss.
Claim 8
Dependent Claim
27 words
The invention as defined in claim 3 wherein said exhaust outlet and said power turbine inlet and outlet and intermediate connections are insulated to minimize energy loss.
Claim 9
Dependent Claim
12 words
The invention as defined in claim 1 wherein said fan is multistage.
Claim 10
Dependent Claim
12 words
The invention as defined in claim 1 wherein said compressor is multistage.
Claim 11
Dependent Claim
12 words
The invention as defined in claim 1 wherein said turbine is multistage.
Claim 12
Dependent Claim
13 words
The invention as defined in claim 1 wherein said power turbine is multistage.
Claim 13
Dependent Claim
20 words
The invention as defined in claim 1 and comprising an intercooler disposed between said compressor and said internal combustion engine.
Claim 14
Dependent Claim
35 words
The invention as defined in claim 1 and comprising a heat exchanger for cooling said internal combustion engine, said heat exchanger being of the type possessing low heat rejection features, thereby minimizing engine heat loss.
Claim 15
Dependent Claim
15 words
The invention as defined in claim 1 wherein said fan and said compressor are coaxial.
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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) | 1992-03-27 | 1992-09-26 | 1993-03-28 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1996-03-27 | 1996-09-26 | 1997-03-28 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2000-03-27 | 2000-09-26 | 2001-03-28 | $7700.00 | Window Closed / Lapsed |