US4274253A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Control for turbine and recuperator inlet temperatures
Assignee: Garrett Corp
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Filing: 1977-12-22
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Granted: 1981-06-23
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Expires: 1997-12-22
Abstract
Abstract A recuperated gas turbine engine control and method which provides improved idling and limits both turbine inlet temperature and recuperator inlet temperature to different, preselected maximum levels.
Inventors
- 👤 Frederic E. Bolliger
- 👤 Geoffrey D. Woodhouse
- 👤 George B. Mattson
- 👤 Bruce S. Anson
- 👤 Robert A. Hatch
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-28 20:04
CPC Classifications
F; F02; F02C; F02C9/00; F02C9/26; F02C6/00; F02C6/20; F02C9/48; F02C9/50; F02C9/54; F02B; F02B1/00; F02B1/02; F02B1/04
Claims Analysis
Total Claims: 8
Claim 1
Independent Claim
227 words
A free turbine type gas turbine engine, comprising: a gas generator having an air inlet, a compressor, a combustor, a turbine, and a drive shaft interconnecting the turbine and compressor; means for delivering fuel to said combustor to maintain a combustion process therein and produce a motive gas output flow to said gas generator turbine; a power turbine section downstream of said gas generator turbine and driven by said output gas flow and having a power output shaft; means for adjusting the incidence of said motive gas output flow onto said power turbine section to alter power transmitted to drive said power turbine section drive shaft; means for sensing the speed of said gas generator section drive shaft, the temperature of said motive gas output delivered to said gas generator turbine, and the temperature of the motive gas flow being exhausted from said power turbine section; and control means operatively coupled with said sensing means for controlling fuel flow to said gas generator section in relation to the sensed speed of said gas generator section, and for controlling said adjusting means in relation to the sensed temperature of said motive gas output flow delivered to said gas generator turbine and the temperature of said motive gas flow exhausted from said power turbine section to prevent either of said sensed temperatures from exceeding preselected, different maximum values thereof.
Claim 2
Dependent Claim
227 words
A free turbine type gas turbine engine, comprising: a gas generator having an air inlet, a compressor, a combustor, a turbine, and a drive shaft interconnecting the turbine and compressor; means for delivering fuel to said combustor to maintain a combustion process therein and produce a motive gas output flow to said gas generator turbine; a power turbine section downstream of said gas generator turbine and driven by said output gas flow and having a power output shaft; means for adjusting the incidence of said motive gas output flow onto said power turbine section to alter power transmitted to drive said power turbine section drive shaft; means for sensing the speed of said gas generator section drive shaft, the temperature of said motive gas output delivered to said gas generator turbine, and the temperature of the motive gas flow being exhausted from said power turbine section; and control means operatively coupled with said sensing means for controlling fuel flow to said gas generator section in relation to the sensed speed of said gas generator section, and for controlling said adjusting means in relation to the sensed temperature of said motive gas output flow delivered to said gas generator turbine and the temperature of said motive gas flow exhausted from said power turbine section to prevent either of said sensed temperatures from exceeding preselected, different maximum values thereof.
Claim 3
Dependent Claim
59 words
A gas turbine engine as set forth in claim 1, wherein said control means are operable to maintain the speed of said gas generator at a first preselected minimum idle speed during idling operation, said control means including means selectively energizable for maintaining gas generator speed at a second, preselected idle speed substantially higher than said first idle speed.
Claim 4
Dependent Claim
27 words
A gas turbine engine as set forth in claim 2, wherein said control means includes a fuel lever for metering fuel flow to said gas generator section.
Claim 5
Dependent Claim
32 words
A gas turbine engine as set forth in claim 3, wherein said selectively energizable means includes a uni-directional solenoid having a plunger engageable with said fuel lever upon energization of said solenoid.
Claim 6
Dependent Claim
31 words
A gas turbine engine as set forth in claim 1, wherein said adjusting means comprises a set of variable incidence guide vanes disposed in the path of said motive gas flow.
Claim 7
Independent Claim
164 words
A method of operating a free turbine type gas turbine engine having a gas generator section and a power turbine section, said method comprising the steps of: delivering fuel flow to the gas generator section to maintain a combustion process therein and produce a motive gas output floww therefrom for sequentially driving a turbine of the gas generator section and said power turbine section; sensing the speed of the gas generator section, the temperature of input motive gas flow delivered to the turbine of said gas generator section, and the temperature of motive gas flow being exhausted from the power turbine section; controlling fuel flow to the gas generator section in relation to the sensed speed of the gas generator section; and adjusting the incidence of motive output flow onto the power turbine section to alter the power transmitted to said power turbine section in relation to both of said sensed temperatures to maintain both said sensed temperatures below preselected, different maximum values thereof.
Claim 8
Independent Claim
164 words
A method of operating a free turbine type gas turbine engine having a gas generator section and a power turbine section, said method comprising the steps of: delivering fuel flow to the gas generator section to maintain a combustion process therein and produce a motive gas output floww therefrom for sequentially driving a turbine of the gas generator section and said power turbine section; sensing the speed of the gas generator section, the temperature of input motive gas flow delivered to the turbine of said gas generator section, and the temperature of motive gas flow being exhausted from the power turbine section; controlling fuel flow to the gas generator section in relation to the sensed speed of the gas generator section; and adjusting the incidence of motive output flow onto the power turbine section to alter the power transmitted to said power turbine section in relation to both of said sensed temperatures to maintain both said sensed temperatures below preselected, different maximum values thereof.
References Cited (Backward Citations)
US3199293A
Cited
US3383090A
Cited
US3521446A
Cited
US3606754A
Cited
US3952502A
Cited
US3999374A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1984-06-22 | 1984-12-22 | 1985-06-23 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1988-06-22 | 1988-12-22 | 1989-06-23 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1992-06-22 | 1992-12-22 | 1993-06-23 | $7700.00 | Window Closed / Lapsed |