Patent US1271222A successfully refreshed from Google Patents.
US4598542A
Expired / Lapsed
US
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Gas turbine power plant
Assignee: Rolls Royce PLC
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Filing: 1984-12-13
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Granted: 1986-07-08
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Expires: 2004-12-13
Abstract
Abstract A gas turbine engine is of a size suitable for generating electrical and heat energy for domestic and other purposes. The engine has a low number of components, and some of the components are capable of performing more than one function. For example, the engine has a centrifugal compressor driven by a centripetal turbine through a shaft. The compressor and turbine are mounted in a casing comprising a two part core and two end plates. The gas flow ducting is formed by surfaces on the compressor and turbine rotors, the core and the two end plates.
Inventors
- 👤 Graham A. Reynolds
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-05 21:58
CPC Classifications
F; F02; F02C; F02C9/00; F02C9/48; F02C9/56; F01; F01D; F01D25/00; F01D25/24; F01D9/00; F01D9/02; F01D9/026; F01D9/04; F02C3/00; F02C3/04; F02C3/10; F02C3/103; F02C6/00; F02C6/18; Y; Y02; Y02E; Y02E20/00; Y02E20/14
Claims Analysis
Total Claims: 6
Claim 1
Independent Claim
180 words
A gas turbine engine comprising; a compressor-turbine housing formed of a ceramic material; a compressor positioned at one end of said housing; a turbine positioned at the opposite end of said housing from said compressor; a shaft interconnecting said compressor to said turbine, said shaft being journaled in said housing in a gas bearing; a combustion arrangement secured to said housing for receiving compressed air from said compressor and a flow of fuel, said combustion arrangement discharging the products of combustion to said turbine through said housing; a diffuser housing connected to said compressor-turbine housing for defining the outer surface of an annular diffuser; said outer surface including a plurality of guide vanes; a bullet defining the inner surface of said annular diffuser, a plurality of turbine blades positioned on said bullet downstream of said guide vanes to thereby form a power turbine, said products of combustion from said turbine flowing into said diffuser and through said power turbine to thereby impart rotational energy to said bullet; and means for converting the rotational energy of said power turbine to work.
Claim 2
Dependent Claim
180 words
A gas turbine engine comprising; a compressor-turbine housing formed of a ceramic material; a compressor positioned at one end of said housing; a turbine positioned at the opposite end of said housing from said compressor; a shaft interconnecting said compressor to said turbine, said shaft being journaled in said housing in a gas bearing; a combustion arrangement secured to said housing for receiving compressed air from said compressor and a flow of fuel, said combustion arrangement discharging the products of combustion to said turbine through said housing; a diffuser housing connected to said compressor-turbine housing for defining the outer surface of an annular diffuser; said outer surface including a plurality of guide vanes; a bullet defining the inner surface of said annular diffuser, a plurality of turbine blades positioned on said bullet downstream of said guide vanes to thereby form a power turbine, said products of combustion from said turbine flowing into said diffuser and through said power turbine to thereby impart rotational energy to said bullet; and means for converting the rotational energy of said power turbine to work.
Claim 3
Dependent Claim
24 words
The gas turbine engine of claim 1 wherein said bullet of said power turbine is journaled to said diffuser housing by a gas bearing.
Claim 4
Dependent Claim
22 words
The gas turbine engine of claim 1 wherein said turbine in said compressor-turbine housing is supported therein by a gas thrust bearing.
Claim 5
Dependent Claim
28 words
The gas turbine engine of claim 1 further comprising a heat exchanger, and means for directing the discharge products passing through said power turbine past the heat exchanger.
Claim 6
Dependent Claim
53 words
The gas turbine engine of claim 1 wherein said turbine-compressor housing comprises a compressor exhaust volute integrally formed therein for directing the compressed air from said compressor to said combustion arrangement and said compressor-turbine housing comprising a turbine inlet volute for directing the products of combustion of said combustion arrangement to said turbine.
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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) | 1989-07-07 | 1990-01-06 | 1990-07-08 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1993-07-07 | 1994-01-06 | 1994-07-08 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1997-07-07 | 1998-01-06 | 1998-07-08 | $7700.00 | Window Closed / Lapsed |