Patent US4055997A successfully refreshed from Google Patents.
US4055997A
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Means for calculating turbine inlet temperature of a gas turbine engine
Assignee: RTX Corp
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Filing: 1976-09-15
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Granted: 1977-11-01
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Expires: 1996-09-15
Abstract
Abstract Turbine inlet temperature of a gas turbine engine is calculated from compressor discharge temperature, total and static pressures and total fuel metered to the engine by combining a sensed engine temperature with a derived fuel/air ratio and from the empirical burner can temperature rise equation solving for the turbine inlet temperature value.
Inventors
- 👤 John Kniat
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-30 03:15
CPC Classifications
F; F02; F02C; F02C9/00; F02C9/26; F02C9/28; F05; F05D; F05D2270/00; F05D2270/01; F05D2270/11; F05D2270/112; F05D2270/30; F05D2270/301; F05D2270/3013; F05D2270/303; F05D2270/70; F05D2270/71
Claims Analysis
Total Claims: 6
Claim 1
Independent Claim
131 words
Means for ascertaining the turbine inlet temperature of a gas turbine engine including computing means responsive to compressor discharge total and static pressure for producing a first signal indicative of the ratio thereof, function generator means responsive to said first signal for producing a second signal indicative of corrected air flow at the burner of said engine, computer means responsive to said second signal and compressor discharge total pressure and total temperature for producing a third signal indicative of air flow at the burner, means responsive to said third signal and fuel flow to said burner for producing a fourth signal indicative of the fuel-air ratio at the burner and means responsive to said fourth signal and compressor discharge total temperature for producing an output signal indicative of turbine inlet temperature.
Claim 2
Dependent Claim
131 words
Means for ascertaining the turbine inlet temperature of a gas turbine engine including computing means responsive to compressor discharge total and static pressure for producing a first signal indicative of the ratio thereof, function generator means responsive to said first signal for producing a second signal indicative of corrected air flow at the burner of said engine, computer means responsive to said second signal and compressor discharge total pressure and total temperature for producing a third signal indicative of air flow at the burner, means responsive to said third signal and fuel flow to said burner for producing a fourth signal indicative of the fuel-air ratio at the burner and means responsive to said fourth signal and compressor discharge total temperature for producing an output signal indicative of turbine inlet temperature.
Claim 3
Dependent Claim
28 words
Means as defined in claim 1 including a computer means for multiplying, dividing and square rooting said compressor discharge total pressure and temperature for producing said third signal.
Claim 4
Dependent Claim
58 words
Means as defined in claim 1 wherein said last mentioned means includes computing means resolving the equation: T.sub.3 + K.sub.1 (K.sub.2 T.sub.3 + K.sub.3)f/a + K.sub.4 where T 3 = total burner inlet temperature f/a = fuel to air ratio at the burner, and K 1 , K 2 , K 3 + K 4 = design constants.
Claim 5
Independent Claim
145 words
The method of calculating the turbine inlet temperature of a gas turbine engine including the steps of: computing a ratio whose value indicative of compressor discharge static to total pressure, generating a function of said ratio obtained in the step of computing indicative of corrected air flow in the burner, computing the air flow value obtained in the step of generating that function by eliminating the correction values, dividing the value obtained in the step of computing the air flow value by the actual amount of fuel being metered to the engine, computing the value of turbine inlet temperature by resolving the equation: T.sub.3 + K.sub.1 (K.sub.2 T.sub.3 + K.sub.3) f/a + K.sub.4 where T 3 = total burner inlet temperature f/a = fuel to air ratio at the burner, and K 1 , K 2 , K 3 + K 4 = design constants.
Claim 6
Independent Claim
145 words
The method of calculating the turbine inlet temperature of a gas turbine engine including the steps of: computing a ratio whose value indicative of compressor discharge static to total pressure, generating a function of said ratio obtained in the step of computing indicative of corrected air flow in the burner, computing the air flow value obtained in the step of generating that function by eliminating the correction values, dividing the value obtained in the step of computing the air flow value by the actual amount of fuel being metered to the engine, computing the value of turbine inlet temperature by resolving the equation: T.sub.3 + K.sub.1 (K.sub.2 T.sub.3 + K.sub.3) f/a + K.sub.4 where T 3 = total burner inlet temperature f/a = fuel to air ratio at the burner, and K 1 , K 2 , K 3 + K 4 = design constants.
References Cited (Backward Citations)
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1980-10-31 | 1981-05-02 | 1981-11-01 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1984-10-31 | 1985-05-02 | 1985-11-01 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1988-10-31 | 1989-05-02 | 1989-11-01 | $7700.00 | Window Closed / Lapsed |