Patent US4494372A successfully refreshed from Google Patents.
US4494372A
Expired / Lapsed
US
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Multi role primary/auxiliary power system with engine start capability for aircraft
Assignee: Lockheed Martin Corp
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Filing: 1983-06-10
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Granted: 1985-01-22
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Expires: 2003-06-10
Abstract
Abstract The invention is a multi role primary/auxiliary power system with engine start capability for aircraft that provides electric, mechanical and air conditioning power as well as engine starting functions. The compressor (20), turbine (26) and motor/generator (24) are coupled to a drive shaft (14) of the aircraft's engine (12) with the motor/generator (24) mounted between the compressor (20) and turbine (26). A first clutch (28) is mounted on the drive shaft (14) between the motor/generator (24) and the turbine (26). Coupled to the outlet (29) of the compressor (20) is a two-way valve (34) adapted to couple the compressor (20) to either a first duct (36) or second duct (37). Both of these ducts (36), (37) are coupled at their opposite ends to the turbine (26). Mounted in the first duct (36) is a combustor (40) and in the second duct (37) a first heat exchanger (42). A third duct (44) is also coupled between the compressor (20) and the turbine (26) and which incorporates a valve (50). Mounted between the turbine (26) and the engine (12) is a gear reduction assembly (58). Coupled to the output of the turbine (26) is a fourth duct (100) which is coupled to a second two-way valve. The second two-way valve (102) either couples the fourth duct (100) to an overboard vent (104) or a fifth duct (106), having a heat exchanger (108) mounted therein to the cabin of the aircraft. Coupling the first, second and third ducts (36), (37), and (44) together is a bypass duct (110) (sixth duct) which bypasses the turbine (26) and connects to the fourth duct (100). The sixth duct (110) also incorporates a simple open/close valve (112). Finally, a control circuit (115) for the motor/generator is provided which can couple either onboard battery power or ground supply AC power to the motor/generator.
Inventors
- 👤 Michael J. Cronin
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-01 14:59
CPC Classifications
F; F02; F02C; F02C7/00; F02C7/32; B; B64; B64D; B64D13/00; B64D13/06; F02C7/26; F02C7/268; B64D2013/0603; B64D2013/0659; B64D2013/0696; F05; F05D; F05D2220/00; F05D2220/50; F05D2260/00; F05D2260/40; F05D2260/404; Y; Y02; Y02T; Y02T50/00; Y02T50/50
Claims Analysis
Total Claims: 10
Claim 1
Independent Claim
158 words
A multi role primary/auxiliary power system for an aircraft having at least one engine, said engine having a drive shaft, said power system comprising: a turbine coupled to said drive shaft; a compressor coupled to said drive shaft; a motor/generator coupled to said drive shaft, said motor/generator mounted between said compressor and said turbine; first passage means coupling the outlet of said compressor to said inlet of said turbine; a combustor mounted in said first passage means; first clutch means mounted on said drive shaft adapted to disengage said motor/generator from said turbine; a second passage means coupled to the outlet of said turbine and adapted to vent the output of said turbine overboard; third passage means coupling said second passage means to the cabin of said aircraft; and first valve means mounted in said second passage means adapted to close off the flow overboard in said second passage means and direct it to said third passage means.
Claim 2
Dependent Claim
158 words
A multi role primary/auxiliary power system for an aircraft having at least one engine, said engine having a drive shaft, said power system comprising: a turbine coupled to said drive shaft; a compressor coupled to said drive shaft; a motor/generator coupled to said drive shaft, said motor/generator mounted between said compressor and said turbine; first passage means coupling the outlet of said compressor to said inlet of said turbine; a combustor mounted in said first passage means; first clutch means mounted on said drive shaft adapted to disengage said motor/generator from said turbine; a second passage means coupled to the outlet of said turbine and adapted to vent the output of said turbine overboard; third passage means coupling said second passage means to the cabin of said aircraft; and first valve means mounted in said second passage means adapted to close off the flow overboard in said second passage means and direct it to said third passage means.
Claim 3
Dependent Claim
100 words
The multi role primary/auxiliary power system of claim 1 including a gear reduction assembly comprising: a second clutch means mounted on said drive shaft between said turbine and said engine; a third clutch means mounted between said second clutch means and said engine; a gear reduction train having an input gear coupled to said drive shaft between said second and third clutch means; and an output gear coupled to said drive shaft between said third clutch means and said engine; and a fourth clutch means coupled to said gear train adapted to allow said gear train to freewheel when disengaged.
Claim 4
Dependent Claim
46 words
The multi role primary/auxiliary power system as set forth in claim 1 further comprising: a fourth passage means coupling said compressor to said turbine; and a second valve means mounted to said fourth passage means adapted to control the airflow from said compressor to said turbine.
Claim 5
Dependent Claim
63 words
The multi role primary/auxiliary power system as set forth in claim 3 including: a fifth passage means coupling said compressor to said turbine; a heat exchanger mounted in said fifth passage means; and third valve means mounted to said first and fifth passage means adapted to control the flow of pressurized air from said compressor to either said first or fifth passage means.
Claim 6
Dependent Claim
48 words
The multi role primary/auxiliary power system as set forth in claim 4 including: sixth passage means coupling said first, fourth and fifth passage means to said second passage means; and fourth valve means mounted in said sixth passage means to control the flow in said sixth passage means.
Claim 7
Dependent Claim
55 words
The multi role primary/auxiliary power system as set forth in claim 5 including: a second heat exchanger mounted in said third passage means, a bypass duct coupled to said third passage means bypassing said second heat exchanger; and fifth valve means mounted in said bypass duct adapted to modulate flow around said second heat exchanger.
Claim 8
Dependent Claim
25 words
The multi role primary/auxiliary power system as set forth in claim 5 wherein said first, second, third and fourth clutch means are electrical mechanical clutches.
Claim 9
Dependent Claim
184 words
A multi role primary/auxiliary power system for an aircraft having at least one engine, said engine having a drive shaft, said power system comprising: a turbine coupled to said drive shaft; a compressor coupled to said drive shaft; a motor/generator coupled to said drive shaft, said motor/generator mounted between said compressor and said turbine; first passage means coupling the outlet of said compressor to said inlet of said turbine; a combustor mounted in said first passage means; first clutch means mounted on said drive shaft adapted to disengage said motor/generator from said turbine; and a gear reduction assembly comprising: a second clutch means mounted on said drive shaft between said turbine and said engine; a third clutch means mounted between said second clutch means and said engine; a gear reduction train having an input gear coupled to said drive shaft between said second and said third clutch means; an output gear coupled to said drive shaft between said third clutch means and said engine; and a fourth clutch means coupled to said gear train adapted to allow said gear train to freewheel when disengaged.
Claim 10
Dependent Claim
184 words
A multi role primary/auxiliary power system for an aircraft having at least one engine, said engine having a drive shaft, said power system comprising: a turbine coupled to said drive shaft; a compressor coupled to said drive shaft; a motor/generator coupled to said drive shaft, said motor/generator mounted between said compressor and said turbine; first passage means coupling the outlet of said compressor to said inlet of said turbine; a combustor mounted in said first passage means; first clutch means mounted on said drive shaft adapted to disengage said motor/generator from said turbine; and a gear reduction assembly comprising: a second clutch means mounted on said drive shaft between said turbine and said engine; a third clutch means mounted between said second clutch means and said engine; a gear reduction train having an input gear coupled to said drive shaft between said second and said third clutch means; an output gear coupled to said drive shaft between said third clutch means and said engine; and a fourth clutch means coupled to said gear train adapted to allow said gear train to freewheel when disengaged.
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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) | 1988-01-22 | 1988-07-23 | 1989-01-22 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1992-01-22 | 1992-07-23 | 1993-01-22 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1996-01-22 | 1996-07-23 | 1997-01-22 | $7700.00 | Window Closed / Lapsed |