Patent US5732546A successfully refreshed from Google Patents.
US5732546A
Expired / Lapsed
US
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Transient turbine overtemperature control
Assignee: General Electric Co
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Filing: 1996-07-19
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Granted: 1998-03-31
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Expires: 2016-07-19
Abstract
Abstract A gas turbine engine includes a compressor joined to a turbine by a core rotor, with a combustor disposed therebetween for receiving compressed air from the compressor and fuel through a valve for producing combustion gas discharged to the turbine. A speed sensor measures speed of the core rotor, and a pressure sensor measures pressure at an inlet to the compressor. A controller is operatively joined to the sensors and the fuel valve and is configured for limiting fuel flow to the combustor in response to core acceleration rate and compressor inlet pressure to limit transient temperature of the combustor discharge combustion gas.
Inventors
- 👤 Ferderick J. Pineo
- 👤 Thomas A. Baxter
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-05 06:35
CPC Classifications
F; F02; F02C; F02C9/00; F02C9/26; F02C9/28; F05; F05D; F05D2270/00; F05D2270/01; F05D2270/04; F05D2270/042; F05D2270/11; F05D2270/112; F05D2270/30; F05D2270/301; F05D2270/3011
Claims Analysis
Total Claims: 14
Claim 1
Independent Claim
91 words
A method of limiting transient turbine overtemperature in a gas turbine engine having a compressor joined to a turbine by a core rotor, with a combustor disposed therebetween for receiving compressed air from said compressor and fuel through a valve for producing combustion gas discharged to said turbine, comprising limiting fuel flow to said combustor in response to a ratio of core acceleration of said core rotor and inlet pressure of inlet air entering said compressor to limit transient temperature of said combustion gas discharged from said combustor into said turbine.
Claim 2
Independent Claim
91 words
A method of limiting transient turbine overtemperature in a gas turbine engine having a compressor joined to a turbine by a core rotor, with a combustor disposed therebetween for receiving compressed air from said compressor and fuel through a valve for producing combustion gas discharged to said turbine, comprising limiting fuel flow to said combustor in response to a ratio of core acceleration of said core rotor and inlet pressure of inlet air entering said compressor to limit transient temperature of said combustion gas discharged from said combustor into said turbine.
Claim 3
Dependent Claim
86 words
A method according to claim 1 further comprising: measuring speed of said core rotor; measuring pressure of said compressor inlet air; comparing said measured speed with a schedule of said ratio of said core acceleration and said compressor inlet pressure versus said rotor speed to obtain therefrom a limiting value of said ratio; multiplying said limiting ratio and said measured pressure to obtain a limiting value of said core acceleration; and limiting said fuel flow to prevent said core rotor from exceeding said limiting core acceleration.
Claim 4
Dependent Claim
44 words
A method according to claim 2 wherein said schedule defines maximum allowable temperatures of said combustion gas over an entire range of operation of said rotor speed, and said limiting acceleration is selected to limit said fuel flow to prevent exceeding said maximum temperatures.
Claim 5
Dependent Claim
22 words
A method according to claim 3 wherein said core rotor speed and acceleration are uncorrected by temperature of said compressor inlet air.
Claim 6
Dependent Claim
23 words
A method according to claim 3 wherein said core rotor speed and acceleration rate are corrected by temperature of said compressor inlet air.
Claim 7
Dependent Claim
30 words
A method according to claim 3 wherein said limiting core acceleration affects said fuel flow only during transient operation of said core rotor and not during steady state operation thereof.
Claim 8
Dependent Claim
86 words
A gas turbine engine comprising: a compressor joined to a turbine by a core rotor; a combustor disposed between said compressor and turbine for receiving compressed air from said compressor and fuel through a valve for producing combustion gas discharged to said turbine; means for limiting fuel flow to said combustor in response to a ratio of acceleration of said core rotor and inlet pressure of inlet air entering said compressor to limit transient temperature of said combustion gas discharged from said combustor into said turbine.
Claim 9
Dependent Claim
86 words
A gas turbine engine comprising: a compressor joined to a turbine by a core rotor; a combustor disposed between said compressor and turbine for receiving compressed air from said compressor and fuel through a valve for producing combustion gas discharged to said turbine; means for limiting fuel flow to said combustor in response to a ratio of acceleration of said core rotor and inlet pressure of inlet air entering said compressor to limit transient temperature of said combustion gas discharged from said combustor into said turbine.
Claim 10
Dependent Claim
126 words
An engine according to claim 7 further comprising: a speed sensor adjoining said core rotor for measuring speed of said rotor; a pressure sensor adjoining an inlet of said compressor for measuring pressure of said compressor inlet air; and wherein said limiting means comprises a programmable controller operatively joined to said speed and pressure sensors and fuel valve, and is configured for: comparing said measured speed with a schedule of said ratio of said core acceleration and said compressor inlet pressure versus said rotor speed to obtain therefrom a limiting value of said ratio; multiplying said limiting ratio and said measured pressure to obtain a limiting value of said core acceleration; and limiting said fuel flow to prevent said rotor from exceeding said limiting core acceleration.
Claim 11
Dependent Claim
44 words
An engine according to claim 8 wherein said schedule defines maximum allowable temperatures of said combustion gas over an entire range of operation of said rotor speed, and said limiting acceleration is selected to limit said fuel flow to prevent exceeding said maximum temperatures.
Claim 12
Dependent Claim
22 words
An engine according to claim 9 wherein said core rotor speed and acceleration are uncorrected by temperature of said compressor inlet air.
Claim 13
Dependent Claim
22 words
An engine according to claim 9 wherein said core rotor speed and acceleration are corrected by temperature of said compressor inlet air.
Claim 14
Dependent Claim
30 words
An engine according to claim 9 wherein said limiting core acceleration affects said fuel flow only during transient operation of said core rotor and not during steady state operation thereof.
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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) | 2001-03-30 | 2001-09-29 | 2002-03-31 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 2005-03-30 | 2005-09-29 | 2006-03-31 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2009-03-30 | 2009-09-29 | 2010-03-31 | $7700.00 | Window Closed / Lapsed |