GB1404501A - Reheat fuel systems for gas turbine engines - Google Patents
Reheat fuel systems for gas turbine enginesInfo
- Publication number
- GB1404501A GB1404501A GB21772A GB21772A GB1404501A GB 1404501 A GB1404501 A GB 1404501A GB 21772 A GB21772 A GB 21772A GB 21772 A GB21772 A GB 21772A GB 1404501 A GB1404501 A GB 1404501A
- Authority
- GB
- United Kingdom
- Prior art keywords
- pressure ratio
- nozzle
- actuator
- error
- control
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/26—Control of fuel supply
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Supercharger (AREA)
Abstract
1404501 Gas turbine jet engine - reheat fuel control ROLLS-ROYCE (1971) Ltd 5 Dec 1972 [4 Jan 1972] 217/72 Heading F1J The invention relates to a re-heat fuel system for a gas turbine jet engine which system is controlled conjointly with a variable area nozzle control system. The engine shown comprises a turbine 16, a reheat fuel system 18 and a variable area nozzle 20 controlled by actuator 38. Reheat control is by means of a pilot lever 22 which is connected to a schedule 24 to which signals such as engine speed and compressor pressure are supplied at 26, 28, the resulting signal passing through line 30 to an actuator 32 which opens fuel valve 34. The actual fuel flow through valve 34 is sensed and fed through line 46 to a comparator 50 where it is compared with the schedule flow, any flow error producing a flow error signal which causes the actuator 32 to adjust the fuel valve 34 to reduce the flow error. The actuator has limits set on its velocity or position which limits are calculated by a device 36 which operates in dependence on turbine pressure ratio error. The variable area nozzle actuator 38 is controlled by a control 40 which also acts to maintain the pressure ratio P3/P6 across the turbine substantially constant. The actual pressure ratio is determined by a sensing unit 44 and this is compared in a comparator 52 with the desired pressure ratio, any resulting pressure ratio error being fed to the nozzle actuator control 40 which causes the nozzle area to be adjusted to reduce the pressure ratio error. A bias term is added to the pressure ratio error signal supplied to the nozzle actuator control 40, the bias term being computed from the reheat fuel flow error in a bias term control 42. The bias term is proportional to the reheat fuel flow error and when added to the pressure ratio error signal produces a higher nozzle actuation signal. As the fuel flow error approaches zero, the bias term to the nozzle loop is removed.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB21772A GB1404501A (en) | 1972-01-04 | 1972-01-04 | Reheat fuel systems for gas turbine engines |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB21772A GB1404501A (en) | 1972-01-04 | 1972-01-04 | Reheat fuel systems for gas turbine engines |
Publications (1)
Publication Number | Publication Date |
---|---|
GB1404501A true GB1404501A (en) | 1975-08-28 |
Family
ID=9700484
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB21772A Expired GB1404501A (en) | 1972-01-04 | 1972-01-04 | Reheat fuel systems for gas turbine engines |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB1404501A (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO1993007373A1 (en) * | 1991-10-11 | 1993-04-15 | Allied-Signal Inc. | Closed loop fuel control system and method |
-
1972
- 1972-01-04 GB GB21772A patent/GB1404501A/en not_active Expired
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO1993007373A1 (en) * | 1991-10-11 | 1993-04-15 | Allied-Signal Inc. | Closed loop fuel control system and method |
US5303541A (en) * | 1991-10-11 | 1994-04-19 | Alliedsignal Inc. | Closed loop fuel control method |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
PS | Patent sealed | ||
PCNP | Patent ceased through non-payment of renewal fee |