Patent US4404794A successfully refreshed from Google Patents.
US4404794A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Turbo-generator for a rotary wing helicopter
Assignee: SOCIETY GESTION PROJET HELICOP-JET Inc
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Filing: 1980-05-21
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Granted: 1983-09-20
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Expires: 2000-05-21
Abstract
Abstract A compressed air turbo-generator comprising a turbo-compressor rotatingly driven by the exhaust gas of a turbo-reactor wherein the longitudinal axes of the turbo-reactor and of the turbo-compressor converge at a gas ejection angled manifold extending from the housing of fixed and rotary crowns of the compressor. The compressor is mounted under the turbo-reactor. The turbo-generator is particularly appropriate for use in providing a compressed air supply for the reaction blades of a rotary wing helicopter.
Inventors
- 👤 Charles Dechaux
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-27 17:03
CPC Classifications
B; B64; B64C; B64C27/00; B64C27/04; B64C27/12; B64C27/16; B64C27/18; F; F02; F02C; F02C3/00; F02C3/04; F02C3/10; F02C6/00; F02C6/04; F02C6/06; F04; F04D; F04D25/00; F04D25/02; F04D25/04
Claims Analysis
Total Claims: 6
Claim 1
Independent Claim
201 words
A compressed air turbo-generator for supplying the reaction blades of the rotating wing of a helicopter, comprising a turbo-reactor including a gas exhaust manifold, said turbo-reactor having a longitudinal axis; a turbo-compressor having a longitudinal axis intersecting the longitudinal axis of said turbo-reactor at an actue angle, said turbo-compressor being located adjacent said turbo-reactor; a driving turbine located within the gas exhaust manifold of said turbo-reactor, said turbine including a rotary wheel rotatable about the longitudinal axis of said turbo-compressor; a shaft having one end secured to the rotary wheel of said driving turbine and the other end to said turbo-compressor for the rotation thereof; a tubular member forming part of said turbo-compressor surrounding said shaft; bearing means interposed between said tubular member and said shaft for rotation of said shaft within said tubular member, said bearing means including a rear ball bearing at the rotary wheel of said turbine; and a hinged member pivotably coupled at one end to said turbo-reactor and the other end to said turbo-compressor, said hinged member permitting said turbo-compressor to be pivoted in a plane defined by said longitudinal axis about a point located in the region of the rotary wheel of said driving turbine.
Claim 2
Dependent Claim
201 words
A compressed air turbo-generator for supplying the reaction blades of the rotating wing of a helicopter, comprising a turbo-reactor including a gas exhaust manifold, said turbo-reactor having a longitudinal axis; a turbo-compressor having a longitudinal axis intersecting the longitudinal axis of said turbo-reactor at an actue angle, said turbo-compressor being located adjacent said turbo-reactor; a driving turbine located within the gas exhaust manifold of said turbo-reactor, said turbine including a rotary wheel rotatable about the longitudinal axis of said turbo-compressor; a shaft having one end secured to the rotary wheel of said driving turbine and the other end to said turbo-compressor for the rotation thereof; a tubular member forming part of said turbo-compressor surrounding said shaft; bearing means interposed between said tubular member and said shaft for rotation of said shaft within said tubular member, said bearing means including a rear ball bearing at the rotary wheel of said turbine; and a hinged member pivotably coupled at one end to said turbo-reactor and the other end to said turbo-compressor, said hinged member permitting said turbo-compressor to be pivoted in a plane defined by said longitudinal axis about a point located in the region of the rotary wheel of said driving turbine.
Claim 3
Dependent Claim
48 words
A compressed air turbo-generator as defined by claim 1 wherein said driving turbine further comprises a plurality of fixed blades and a crown having a spherical portion supporting said fixed blades, and wherein said tubular member includes a spherical head pivotable within the spherical portion of said crown.
Claim 4
Dependent Claim
63 words
A compressed air turbo-generator as defined by claim 1 or 2 which further comprises a fixed coaxial sheath surrounding said tubular member, said sheath and tubular member defining an annular space therebetween; and a supply pipe coupling said turbo-reactor to said annular space, said supply pipe conducting high pressure air from said turbo-reaction to said annular space for cooling said rear ball bearing.
Claim 5
Dependent Claim
52 words
A compressed air turbo-generator as defined by claim 1 wherein said turbo-compressor includes a distribution chamber coupled to said annular space, said turbo-generator further including a supply duct coupled to said distribution chamber for supplying low pressure air from said turbo-reactor to the reaction blades of the rotating wing of said helicopter.
Claim 6
Dependent Claim
31 words
A compressed air turbo-generator as defined by claim 2 wherein said turbo-compressor includes a rotor, and wherein said distribution chamber is coaxial therewith, said distribution chamber having a constant radial cross-section.
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) | 1986-09-19 | 1987-03-21 | 1987-09-20 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1990-09-19 | 1991-03-21 | 1991-09-20 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1994-09-19 | 1995-03-21 | 1995-09-20 | $7700.00 | Window Closed / Lapsed |