Patent US3886731A successfully refreshed from Google Patents.
US3886731A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Governing device for a gas turbine system
Assignee: MTU Aero Engines AG
•
Filing: 1972-12-22
•
Granted: 1975-06-03
•
Expires: 1992-12-22
Abstract
Abstract Governing device for a gas turbine system having a speed governor using the speed of a turbine in this system as a regulating variable for varying the fuel flow, characterized in that said speed (N) is automatically variable as a function of the inlet temperature (T1) of the gas turbine system.
Inventors
- 👤 Christian Greune
- 👤 Friedrich Hackl
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-26 10:30
CPC Classifications
F; F02; F02C; F02C9/00; F02C9/26; F02C9/28; F02C9/32
Claims Analysis
Total Claims: 11
Claim 1
Independent Claim
111 words
A governing system for controlling the fuel flow to a gas turbine engine having a combustion chamber receiving compressed air from a compressor and fuel from a fuel metering device, comprising a governor providing a control signal to control said fuel metering device, means for generating a speed correction signal at constant turbine speed or power lever angle in response to the related values of engine speed and temperature at the inlet of said compressor, and a summing junction for summing said speed correction signal and a desired speed signal, the output of said summing junction being applied in control of said governor at constant turbine speed or power lever angle.
Claim 2
Dependent Claim
111 words
A governing system for controlling the fuel flow to a gas turbine engine having a combustion chamber receiving compressed air from a compressor and fuel from a fuel metering device, comprising a governor providing a control signal to control said fuel metering device, means for generating a speed correction signal at constant turbine speed or power lever angle in response to the related values of engine speed and temperature at the inlet of said compressor, and a summing junction for summing said speed correction signal and a desired speed signal, the output of said summing junction being applied in control of said governor at constant turbine speed or power lever angle.
Claim 3
Dependent Claim
111 words
A governing system for controlling the fuel flow to a gas turbine engine having a combustion chamber receiving compressed air from a compressor and fuel from a fuel metering device, comprising a governor providing a control signal to control said fuel metering device, means for generating a speed correction signal at constant turbine speed or power lever angle in response to the related values of engine speed and temperature at the inlet of said compressor, and a summing junction for summing said speed correction signal and a desired speed signal, the output of said summing junction being applied in control of said governor at constant turbine speed or power lever angle.
Claim 4
Dependent Claim
111 words
A governing system for controlling the fuel flow to a gas turbine engine having a combustion chamber receiving compressed air from a compressor and fuel from a fuel metering device, comprising a governor providing a control signal to control said fuel metering device, means for generating a speed correction signal at constant turbine speed or power lever angle in response to the related values of engine speed and temperature at the inlet of said compressor, and a summing junction for summing said speed correction signal and a desired speed signal, the output of said summing junction being applied in control of said governor at constant turbine speed or power lever angle.
Claim 5
Dependent Claim
27 words
A governing system as defined in claim 1, wherein said means for generating said speed correction signal is responsive to the square root of said inlet temperature.
Claim 6
Dependent Claim
30 words
A governing system as defined in claim 1, wherein said engine speed to which said engine speed correction means is responsive is derived from the output shaft of said compressor.
Claim 7
Dependent Claim
40 words
A governing system as defined in claim 1, further including means for regulating said desired speed signal to less than a maximum value including correction means for varying said maximum value in proportion to the inlet temperature of said compressor.
Claim 8
Dependent Claim
25 words
A governing system as defined in claim 4, wherein said correction means varies said maximum value only below a selectived low level of inlet temperature.
Claim 9
Dependent Claim
108 words
A governing system for controlling the fuel flow to a gas turbine engine having a combustion chamber receiving compressed air from a compressor and fuel from a fuel metering device, comprising a governor providing a control signal to control said fuel metering device, a summing junction for summing signals representing engine speed and desired engine speed, the output of said summing junction being applied in control of said governor, and means for regulating said desired speed signal to less than a maximum value including correction means for varying said maximum value in response to the inlet temperature of said compressor at constant turbine speed or power lever angle.
Claim 10
Dependent Claim
108 words
A governing system for controlling the fuel flow to a gas turbine engine having a combustion chamber receiving compressed air from a compressor and fuel from a fuel metering device, comprising a governor providing a control signal to control said fuel metering device, a summing junction for summing signals representing engine speed and desired engine speed, the output of said summing junction being applied in control of said governor, and means for regulating said desired speed signal to less than a maximum value including correction means for varying said maximum value in response to the inlet temperature of said compressor at constant turbine speed or power lever angle.
Claim 11
Dependent Claim
30 words
A governing system as defined in claim 6, wherein said engine speed to which said engine speed correction means is responsive is derived from the output shaft of said compressor.
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) | 1978-06-02 | 1978-12-02 | 1979-06-03 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1982-06-02 | 1982-12-02 | 1983-06-03 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1986-06-02 | 1986-12-02 | 1987-06-03 | $7700.00 | Window Closed / Lapsed |