US2743051A - Gas turbine plant - Google Patents

Gas turbine plant Download PDF

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Publication number
US2743051A
US2743051A US234116A US23411651A US2743051A US 2743051 A US2743051 A US 2743051A US 234116 A US234116 A US 234116A US 23411651 A US23411651 A US 23411651A US 2743051 A US2743051 A US 2743051A
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turbine
compressor
duct
gas
combustion chamber
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US234116A
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Grey John Constantine
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Power Jets Research and Development Ltd
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Power Jets Research and Development Ltd
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    • 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
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/10—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output supplying working fluid to a user, e.g. a chemical process, which returns working fluid to a turbine of the plant

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  • This invention relates to the application of gas turbine plant to the generation for extraneous use, e. g. for blowing a blast furnace, of a supply of combustionsupporting air at a pressure substantially sigher than atmospheric and is more especially concerned with the control of such plant.
  • Plant of the kind with which the invention is concerned comprises a main turbine-driven compressor which provides the extraneous air supply and also feeds a combustion chamber from which the driving turbine receives hot gas; a separate compressor (the gas compressor) driven by the same turbine feeds fuel gas to the combustion chamber.
  • the present invention provides gas turbine plant operating on gaseous fuel and designed for the generation for extraneous use of combustion supporting air at a pressure substantially higher than atmospheric cornprising a main turbine-driven compressor which provides the extraneous air supply and also feeds a combustion chamber from which the driving turbine receives hot gas, a separate turbine-driven compressor for supplying fuel gas to the combustion chamber, characterized in that turbine speed is controlled by diverting fuel gas delivered by the gas compressor before such gas reaches the combustion chamber.
  • the diverting of fuel gas is effected automatically responsive to a variable delivery condition of the main compressor.
  • This invention may best be understood by reference to the diagrammatic drawing which shows a bypass valve so positioned as to control the amount of fuel to a combustion chamber in accordance with the output pressure of the main turbine-driver compressor.
  • the main turbine-driver compressor is automatically controlled to accommodate changing load conditions.
  • valve member 18 permit the passage of gas to the combustion chamber 16.
  • the position of the valve member 18 of the by-pass valve is controlled by an hydraulic relay 19,the supply to which of liquid from a pump 20 is controlled by a pilot valve 21.
  • said pilot valve 21 is obviously adapted to control the flow of the spent fluid to a reservoir (not shown) to which pump 20 is connected in a closed system.
  • the piston of the relay and that of the valve 21 are linked to one end and an intermediate point respectively of a restoring lever 22, the other end of which is linked to an aneroid capsule 23.
  • the capsule is mounted in a housing 24, the interior'of which is subject, by way of a pipe 25, to the pressure obtaining in the delivery duct 14.
  • control system just described may, of course, be applied to plant differing in detail (for example, one comprising an axial air compressor from which combustion air is bled at an intermediate stage) and offers advantages by way of fuel economy as 'well as of convenience.
  • Gas turbine plant comprising an air compressor, a fuel gas compressor, a turbine, shaft means drivingly connecting the turbine to the said air and fuel gas compressors, a combustion chamber, first duct means conveying compressed air from the said air compressor to provide a supply of compressed air for use extraneously of the plant, second duct means conveying compressed air from the air compressor to the combustion chamber, third duct means conveying fuel gas from the gas compressor to the combustion chamber, fourth duct means conveying combustion gases from the combustion chamber to the turbine, at diverting duct positioned in the said third duct means enabling fuel gas tobe diverted from the said third duct means instead of passing to the combustion chamber, valve means controlling the How of fuel gas from the third duct means into the said diverting duct, actuating means for the valve means, a first operative connection between the.
  • control device actuating means and the valve means, a control device, a second operative connection between the control device and the actuating means and a connection between the control device and the said first duct means enabling the control device to be operated in response to variation of a condition of the compressed air delivered by the air compressor.
  • Gas turbine plant comprising an air compressor, a fuel gas compressor, turbine, shaft means drivingly connecting the turbine to the said air and fuel gas compressors, a combustion chamber, first duct means conveying compressed air from the said air compressor to provide a supply of compressed air for use extraneously of the plant, second duct means conveying compressed air from the air compressor to the combustion chamber, third duct means conveying fuel gas from the gas compressor to the combustion chamber, fourth duct means conveying combustion gases from the combustion chamher to the turbine, a diverting duct positioned in the said third duct means enabling fuel gas to be diverted from the said third duct means instead of passing to h combustion chambe valvemeans controlling the flow of fuel gas from the, third duct means into the said diverting duct, actuating means for the valve means, a first operative connection between the actuating means and the valve means, .a pressure-sensitive control device, a second operative connection between the control device and the actuating means and a connection between the control device and the said first duct means enabling
  • Gas turbine plant comprising an air compressor, a fuel gas compressor, a turbine, shaft means drivingly connecting the turbine tothe said air and fuel gas coma pressors, a combustion chamber, first duct means conveying compressed air from the said air compressor to provide a supply of compressed air for use extraneously of the plant, second duct means conveying compressed air from the air compressor to the combustion chamber, third duct means conveying fuel. gas from the gas compressor to the combustion chamber, fourth duct means conveying combustion gases from the combustion chamber to the turbine, at diverting duct positioned in the said third duct means enabling fuel gas to be diverted from the said third duct means instead of passing to the combustion chamber, valve means.
  • Blast furnace blowing apparatus incorporating gas turbine plant comprising an air compressor, a fuel gas compressor, a'turbine shaft means drivingly connecting the turbine t the sa d air and fue g s compressors, a combustion chamber, first duct means adapted to convey compressed air from the said air compressor to a blast furnace, second duct means conveying compressed air from the air compressor to, the combustion chamber, third duct means conveying fuel gas from the gas compressor to the combustion chamber, fourth duct means conveying combustion gases from the combustion chamher" to the turbine, a diverting duct positioned in :the
  • said third duct means enabling fuel gas to be diverted from the said third duct means instead of passing to the combustion .chamber, valve, means controlling the flow of fuel gas from the third duct means into the said diverting duct, actuating means for the valve means, a first operative connection between the actuating means and the valve means, a control device, a second operative connection between the control device and the actuating means and a connection between the control device and the said first duct means enabling the control device to be operated in response to variation of a condition of the compressed air delivered by the air compressor.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • General Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Description

April 24, 1956 c, GREY 2,743,051
GAS TURBINE PLANT Filed June 28, 1951 W l v /31 27 Inventor x ngz bumu-M Attorney United States Patent GAS TURBINE PLANT John Constantine Grey, Isleworth, England, assignor to Power Jets (Research & Development) Limited, London, England, a British company Application June 28, 1951, Serial No. 234,116 Claims priority, application Great Britain July 3, 1950 4 Claims. (Cl. 230-9) This invention relates to the application of gas turbine plant to the generation for extraneous use, e. g. for blowing a blast furnace, of a supply of combustionsupporting air at a pressure substantially sigher than atmospheric and is more especially concerned with the control of such plant.
7 Plant of the kind with which the invention is concerned comprises a main turbine-driven compressor which provides the extraneous air supply and also feeds a combustion chamber from which the driving turbine receives hot gas; a separate compressor (the gas compressor) driven by the same turbine feeds fuel gas to the combustion chamber. The control of such plant is complicated when it is necessary for the extraneous air supply to be substantially constant in pressure but variable in amount; mere throttling of the extraneous supply will result in a larger proportion of the delivery of the main compressor being diverted to the combustion chamber, with consequent variation of turbine speed (and thus delivery pressure) while an attempt to vary turbinev inlet temperature (and thus to control turbine speed) by throttling the gas supply to the gas compressor will result in an intolerable pressure differential between the deliveries to the combustion chamber from the gas and main compressors respectively.
The present invention provides gas turbine plant operating on gaseous fuel and designed for the generation for extraneous use of combustion supporting air at a pressure substantially higher than atmospheric cornprising a main turbine-driven compressor which provides the extraneous air supply and also feeds a combustion chamber from which the driving turbine receives hot gas, a separate turbine-driven compressor for supplying fuel gas to the combustion chamber, characterized in that turbine speed is controlled by diverting fuel gas delivered by the gas compressor before such gas reaches the combustion chamber.
Preferably, the diverting of fuel gas is effected automatically responsive to a variable delivery condition of the main compressor.
This invention may best be understood by reference to the diagrammatic drawing which shows a bypass valve so positioned as to control the amount of fuel to a combustion chamber in accordance with the output pressure of the main turbine-driver compressor. Thus, the main turbine-driver compressor is automatically controlled to accommodate changing load conditions.
An example of plant in accordance with the invention is illustrated by the accompanying diagrammatic drawing and comprises a turbine 10 driving a two-stage,
, 2 l and the remainder being passed to a combustion chamber 16 from which the turbine is fed; the gas compressor 11 delivers to the combustion chamber by way of a by-pass valve 17. Dual ports 5 in valve member 18 permit the passage of gas to the combustion chamber 16.
The position of the valve member 18 of the by-pass valve is controlled by an hydraulic relay 19,the supply to which of liquid from a pump 20 is controlled by a pilot valve 21. As is well known in the art, said pilot valve 21 is obviously adapted to control the flow of the spent fluid to a reservoir (not shown) to which pump 20 is connected in a closed system. The piston of the relay and that of the valve 21 are linked to one end and an intermediate point respectively of a restoring lever 22, the other end of which is linked to an aneroid capsule 23. The capsule is mounted in a housing 24, the interior'of which is subject, by way of a pipe 25, to the pressure obtaining in the delivery duct 14.
With the arrangement illustrated, increase, beyond a predetermined value, of pressure within the duct 14 results in the valve member 18 taking up a new position such that a proportion, or a greater proportion as the case may be, of the delivery of the gas compressor 11 is by-passed, being permitted to return, by way of a duct 26, to the reservoir (not shown) from which the gas compressor is fed; the reduction of the fuel supply involves reduction of the turbine inlet temperature and thus of turbine speed, with resultant reduction (i. e restoration) of delivery pressure.
The control system just described may, of course, be applied to plant differing in detail (for example, one comprising an axial air compressor from which combustion air is bled at an intermediate stage) and offers advantages by way of fuel economy as 'well as of convenience.
What I claim is:
1. Gas turbine plant comprising an air compressor, a fuel gas compressor, a turbine, shaft means drivingly connecting the turbine to the said air and fuel gas compressors, a combustion chamber, first duct means conveying compressed air from the said air compressor to provide a supply of compressed air for use extraneously of the plant, second duct means conveying compressed air from the air compressor to the combustion chamber, third duct means conveying fuel gas from the gas compressor to the combustion chamber, fourth duct means conveying combustion gases from the combustion chamber to the turbine, at diverting duct positioned in the said third duct means enabling fuel gas tobe diverted from the said third duct means instead of passing to the combustion chamber, valve means controlling the How of fuel gas from the third duct means into the said diverting duct, actuating means for the valve means, a first operative connection between the. actuating means and the valve means, a control device, a second operative connection between the control device and the actuating means and a connection between the control device and the said first duct means enabling the control device to be operated in response to variation of a condition of the compressed air delivered by the air compressor.
2. Gas turbine plant comprising an air compressor, a fuel gas compressor, turbine, shaft means drivingly connecting the turbine to the said air and fuel gas compressors, a combustion chamber, first duct means conveying compressed air from the said air compressor to provide a supply of compressed air for use extraneously of the plant, second duct means conveying compressed air from the air compressor to the combustion chamber, third duct means conveying fuel gas from the gas compressor to the combustion chamber, fourth duct means conveying combustion gases from the combustion chamher to the turbine, a diverting duct positioned in the said third duct means enabling fuel gas to be diverted from the said third duct means instead of passing to h combustion chambe valvemeans controlling the flow of fuel gas from the, third duct means into the said diverting duct, actuating means for the valve means, a first operative connection between the actuating means and the valve means, .a pressure-sensitive control device, a second operative connection between the control device and the actuating means and a connection between the control device and the said first duct means enabling the control device to be operated in response to variation from a given datum of the pressure of the compressed air delivered by the air compressor.
3. Gas turbine plant comprising an air compressor, a fuel gas compressor, a turbine, shaft means drivingly connecting the turbine tothe said air and fuel gas coma pressors, a combustion chamber, first duct means conveying compressed air from the said air compressor to provide a supply of compressed air for use extraneously of the plant, second duct means conveying compressed air from the air compressor to the combustion chamber, third duct means conveying fuel. gas from the gas compressor to the combustion chamber, fourth duct means conveying combustion gases from the combustion chamber to the turbine, at diverting duct positioned in the said third duct means enabling fuel gas to be diverted from the said third duct means instead of passing to the combustion chamber, valve means. controlling the flow of fuel gas from the third duct means into the said diverting duct, a hydraulic relay, a first operative connection between the hydraulic relay and the valve means, an aneroid capsule, a second operative connection between the aneroid capsule and the hydraulic relay and a connecting pipe between the aneroid capsule and the said first duct means enabling the aneroid capsule to be operated in response to variation from a given datum of the pressure of the compressed air delivered by the air compressor.
4. Blast furnace blowing apparatus incorporating gas turbine plant comprising an air compressor, a fuel gas compressor, a'turbine shaft means drivingly connecting the turbine t the sa d air and fue g s compressors, a combustion chamber, first duct means adapted to convey compressed air from the said air compressor to a blast furnace, second duct means conveying compressed air from the air compressor to, the combustion chamber, third duct means conveying fuel gas from the gas compressor to the combustion chamber, fourth duct means conveying combustion gases from the combustion chamher" to the turbine, a diverting duct positioned in :the
said third duct means enabling fuel gas to be diverted from the said third duct means instead of passing to the combustion .chamber, valve, means controlling the flow of fuel gas from the third duct means into the said diverting duct, actuating means for the valve means, a first operative connection between the actuating means and the valve means, a control device, a second operative connection between the control device and the actuating means and a connection between the control device and the said first duct means enabling the control device to be operated in response to variation of a condition of the compressed air delivered by the air compressor.
References Cited in the file of this patent UNITED STATES PATENTS 2,330,558 Curtis Sept. 28, 1943 2,399,046 Larrecq Apr. 23, 1946 2,416,797 Dodson Mar. 4, 1947 2,422,808 'Stokes June 24, 1947 2,488,969 Dietler Nov. 22, 1949 2,557,526 Bobier June 19, 1951 2,559,814 Whittle July 10, 1951 2,592,749 Sedille Apr. 15, 1952 a 2,621,476 Sedille Dec. 16, 1952 FOREIGN PATENTS 490,978 Great Britain Aug. 24, 1938 941,556 France July 19, 1948
US234116A 1950-07-03 1951-06-28 Gas turbine plant Expired - Lifetime US2743051A (en)

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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2937497A (en) * 1955-03-17 1960-05-24 Power Jets Res & Dev Ltd Gas turbine-driven plant
US3009631A (en) * 1957-04-30 1961-11-21 Power Jets Res & Dev Ltd Control devices for fluid pressure systems
US3229895A (en) * 1964-09-29 1966-01-18 Ingersoll Rand Co Means of loading and controlling reciprocating expansion engines

Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB490978A (en) * 1936-11-03 1938-08-24 Bbc Brown Boveri & Cie Improvements in and relating to the regulation of gas turbines
US2330558A (en) * 1940-03-18 1943-09-28 Curtis Pump Co High altitude fuel system for aircraft
US2399046A (en) * 1940-03-26 1946-04-23 Gen Electric Gas turbine power plant
US2416797A (en) * 1943-09-23 1947-03-04 Dodson Edward Fuel injection system for internalcombustion engines
US2422808A (en) * 1943-06-22 1947-06-24 Hobson Ltd H M Regulating device for controlling the supply of fuel and other liquids to internal-combustion engines
FR941556A (en) * 1947-02-06 1949-01-14 Method for adjusting turbo-reactors and apparatus for implementing this method
US2488969A (en) * 1945-02-27 1949-11-22 Bbc Brown Boveri & Cie Combined gas producer and gas turbine plant
US2557526A (en) * 1949-10-01 1951-06-19 George M Holley Acceleration fuel control responsive to air pressure and temperature, speed, and fuel flow for gas turbines
US2559814A (en) * 1942-11-17 1951-07-10 Power Jets Res & Dev Ltd Cooling combustion-engine air supply by ammonia
US2592749A (en) * 1947-01-16 1952-04-15 Rateau Soc Gas turbine engine associated with a gas producer under pressure
US2621476A (en) * 1942-03-16 1952-12-16 Rateau La Courneuve Soc Gas turbine installation operating on gaseous fuels

Patent Citations (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB490978A (en) * 1936-11-03 1938-08-24 Bbc Brown Boveri & Cie Improvements in and relating to the regulation of gas turbines
US2330558A (en) * 1940-03-18 1943-09-28 Curtis Pump Co High altitude fuel system for aircraft
US2399046A (en) * 1940-03-26 1946-04-23 Gen Electric Gas turbine power plant
US2621476A (en) * 1942-03-16 1952-12-16 Rateau La Courneuve Soc Gas turbine installation operating on gaseous fuels
US2559814A (en) * 1942-11-17 1951-07-10 Power Jets Res & Dev Ltd Cooling combustion-engine air supply by ammonia
US2422808A (en) * 1943-06-22 1947-06-24 Hobson Ltd H M Regulating device for controlling the supply of fuel and other liquids to internal-combustion engines
US2416797A (en) * 1943-09-23 1947-03-04 Dodson Edward Fuel injection system for internalcombustion engines
US2488969A (en) * 1945-02-27 1949-11-22 Bbc Brown Boveri & Cie Combined gas producer and gas turbine plant
US2592749A (en) * 1947-01-16 1952-04-15 Rateau Soc Gas turbine engine associated with a gas producer under pressure
FR941556A (en) * 1947-02-06 1949-01-14 Method for adjusting turbo-reactors and apparatus for implementing this method
US2557526A (en) * 1949-10-01 1951-06-19 George M Holley Acceleration fuel control responsive to air pressure and temperature, speed, and fuel flow for gas turbines

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2937497A (en) * 1955-03-17 1960-05-24 Power Jets Res & Dev Ltd Gas turbine-driven plant
US2955421A (en) * 1955-03-17 1960-10-11 Power Jets Res & Dev Ltd Gas turbine-driven plant
US3009631A (en) * 1957-04-30 1961-11-21 Power Jets Res & Dev Ltd Control devices for fluid pressure systems
US3229895A (en) * 1964-09-29 1966-01-18 Ingersoll Rand Co Means of loading and controlling reciprocating expansion engines

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