GB651319A - Improvements in or relating to gas turbine engine power plants - Google Patents

Improvements in or relating to gas turbine engine power plants

Info

Publication number
GB651319A
GB651319A GB3117648A GB3117648A GB651319A GB 651319 A GB651319 A GB 651319A GB 3117648 A GB3117648 A GB 3117648A GB 3117648 A GB3117648 A GB 3117648A GB 651319 A GB651319 A GB 651319A
Authority
GB
United Kingdom
Prior art keywords
turbine
vanes
low
fuel
chamber
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
Application number
GB3117648A
Inventor
Richard Wigmore Foster-Pegg
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB3117648A priority Critical patent/GB651319A/en
Publication of GB651319A publication Critical patent/GB651319A/en
Expired legal-status Critical Current

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  • Engine Equipment That Uses Special Cycles (AREA)

Abstract

651,319. Gas turbine plant. ROLLSROYCE, Ltd. Dec. 1, 1948, No. 31176. [Class 110(iii)] In a gas turbine plant comprising high and low pressure turbines driving respectively high and low pressure compressors and re-heating between the turbines, the low-pressure turbine has angularly adjustable nozzle guide vanes. These vanes are held at maximum throat area for low loads and regulation of the plant over the whole or part of the higher range of load is effected by adjustment of the nozzle vanes so that the nozzle area increases with increases in the supply of fuel to the re-heat chamber. The exhaust from a high-pressure turbine 19, 21, passes through an air pre-heater 40 and a re-heating chamber 43 before the low pressure turbine 24. At low load, regulation is effected by control of the fuel supply to the combustion chamber 14. At increasing load, turbine 19, 21 will run at constant speed and the adjustable nozzle guide vanes of turbine 24 are moved towards their minimum throat area position. Further power is obtained by opening the preheater byepass valve 42 and finally by admitting fuel to the re-heating chamber 43, the nozzle vanes of the turbine 24 being opened in agreement with the increase of fuel to the chamber 43.
GB3117648A 1948-12-01 1948-12-01 Improvements in or relating to gas turbine engine power plants Expired GB651319A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB3117648A GB651319A (en) 1948-12-01 1948-12-01 Improvements in or relating to gas turbine engine power plants

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB3117648A GB651319A (en) 1948-12-01 1948-12-01 Improvements in or relating to gas turbine engine power plants

Publications (1)

Publication Number Publication Date
GB651319A true GB651319A (en) 1951-03-14

Family

ID=10319147

Family Applications (1)

Application Number Title Priority Date Filing Date
GB3117648A Expired GB651319A (en) 1948-12-01 1948-12-01 Improvements in or relating to gas turbine engine power plants

Country Status (1)

Country Link
GB (1) GB651319A (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2988884A (en) * 1958-09-23 1961-06-20 Pouit Robert Improvements in gas turbine power plants
US3765170A (en) * 1970-12-27 1973-10-16 Toyota Motor Co Ltd Composite gas turbine set
US4858428A (en) * 1986-04-24 1989-08-22 Paul Marius A Advanced integrated propulsion system with total optimized cycle for gas turbines
GB2232720A (en) * 1989-06-15 1990-12-19 Rolls Royce Business Ventures Gas turbine engine power unit
GB2250780A (en) * 1990-12-14 1992-06-17 Rolls Royce Business Ventures Gas turbine engine power unit

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2988884A (en) * 1958-09-23 1961-06-20 Pouit Robert Improvements in gas turbine power plants
US3765170A (en) * 1970-12-27 1973-10-16 Toyota Motor Co Ltd Composite gas turbine set
US4858428A (en) * 1986-04-24 1989-08-22 Paul Marius A Advanced integrated propulsion system with total optimized cycle for gas turbines
GB2232720A (en) * 1989-06-15 1990-12-19 Rolls Royce Business Ventures Gas turbine engine power unit
US5119624A (en) * 1989-06-15 1992-06-09 Rolls-Royce Business Ventures Limited Gas turbine engine power unit
GB2232720B (en) * 1989-06-15 1993-11-10 Rolls Royce Business Ventures Gas turbine engine power unit
GB2250780A (en) * 1990-12-14 1992-06-17 Rolls Royce Business Ventures Gas turbine engine power unit
US5182904A (en) * 1990-12-14 1993-02-02 Rolls-Royce Business Ventures Limited Gas turbine engine power unit

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