US3765169A - Gas turbine equipment and method of controlling such equipment - Google Patents

Gas turbine equipment and method of controlling such equipment Download PDF

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Publication number
US3765169A
US3765169A US00209120A US3765169DA US3765169A US 3765169 A US3765169 A US 3765169A US 00209120 A US00209120 A US 00209120A US 3765169D A US3765169D A US 3765169DA US 3765169 A US3765169 A US 3765169A
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US
United States
Prior art keywords
pressure part
low pressure
inlet guide
guide vanes
gas turbine
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 - Lifetime
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US00209120A
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English (en)
Inventor
B Kyrklund
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ABB Stal AB
Original Assignee
Stal Laval Turbin AB
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Publication date
Application filed by Stal Laval Turbin AB filed Critical Stal Laval Turbin AB
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Publication of US3765169A publication Critical patent/US3765169A/en
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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
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/16—Control of working fluid flow
    • F02C9/20—Control of working fluid flow by throttling; by adjusting vanes
    • F02C9/22—Control of working fluid flow by throttling; by adjusting vanes by adjusting turbine vanes

Definitions

  • F026 3/10 A multiple rotor gas turbine engine comprising a tun [58] Field of Search 60/3916, 39.25, bocompressor a combustion chamber and a turbine 60/3917 3928 having a high pressure part and a low pressure part, the low pressure part driving the turbocompressor [56] References (med while the high pressure part delivers the output power.
  • the inlet direction of the gas in relation to the rotating vanes of the high pressure part of the turbine may be varied, and the opening angle a of the guide vanes may be suitably adjusted in relation to the other control parameters of the equipment, namely the speed n of the low pressure rotor, the output power E and the temperature T of the combination chamber or the fuel injection q.
  • the output power E can be regulated either by means of the opening angle of the inlet vanes or the fuel supply q or the temperature T, whereas the other two parameters are coordinated by means of the'control equipment.
  • FIG. l' shows a gas turbine equipment according to the invention
  • FIGS. 2a and 2b show the system of inlet guide vanes for the high pressure part in detail
  • FIGS. 3a and 3b and FIGS. 4a and 4b show various control circuits for the equipment according to the invention.
  • FIG. I shows a gas turbine engine comprising a turbocompressor l, a combustion chamber 2 and a turbine section comprising a high pressure part 3 and a low pressure part 4.
  • The-latter drives the turbo compressor via a shaft 5, whereas the high pressure part delivers the output power to the generator 6 via a shaft 7.
  • the compressed air from the compressor 1 is supplied to the combustion chamber 2 through a conduit 8.
  • Fuel is supplied to the combustion chamber via a control valve 9.
  • the low pressure part is provided with at least one rotating vane wheel and its r.p.m. is measured with the help of a tachometer-generator 12.
  • the high pressure part is provided with at least one disc carrying a row of blades row 10, in front of which is arranged a system '11 of inlet guide vanes, Le, a system of guide vanes having variable opening angles a, as can be seen-in more detail in FIG. 2b.
  • FIGS. 2a and 2b show part of the inlet guide vane system 11 with the blade row 10, FIG. 2a showing these parts seen from the side in an axial section and FIG. 2b showing the same parts seen from the outside in radial direction.
  • the vane system 11 consists of a system of pivotable guide vanes 25, each arranged on a shaft 22 provided with a transverse pin 23. These transverse pins fit into holders on the inside of a cylindrical ring 24 which can be turned by a servo-device 19. The turning of the ring 24 also turns the transverse pins 23 and consequently the guide vanes 25 so that their opening angles a may be varied.
  • the variables which are coordinated in relation to each other in the control system of the turbine equipment are the output power E, the rpm. n of the low pressure part,the fuel supply q and the opening angle a for the inlet guide vane system of the high pressure part, as mentioned previously. These four parameters can be regulated in accordance with different principles, as exemplified in FIGS. 3a, 3b and FIGS. 4a, 4b.
  • the valve 9 for the fuel supply is regulated by means of a servo-device 17 from a frequency/power control circuit.
  • the generator 6 is for this purpose provided with a frequency gauge 20 and a power gauge 13.
  • the true value and the desired value for the power are supplied to an amplifier 14, the output signal of which is supplied to a second amplifier 16 connected in parallel with the signal from the frequency gauge 20. In this way the fuel supply through the valve 9 is regulated in accordance with the desired frequency and power.
  • the angle a of the inlet guide vane system is controlled by the speed n of the low pressure part in accordance with FIG. 3b so that each value for n is allotted a certain angle a.
  • the speed n is measured by a tachometer-generator 12, the output signal of which is converted in an amplifier 18 to form the control signal for the servomotor 19 which adjusts the angle a of the guide vane system.
  • FIG. 4b shows how the speed is measured by a tachometer-generator 12, the output signal of which is compared in the amplifier 16 with a desired value from a transducer 21.
  • the output signal of the amplifier provides the control signal for the servomotor 17 of the fuel valve 9.
  • the power of the turbine equipment is controlled with the help of the angle a of the inlet guide vane system according to FIG. 4a, this figure showing how the servomotor 19 of the system is affected by the frequency/power control circuit 20, 13 15.
  • a multiple gas turbine engine comprising a turbocompressor, a combustion section and a turbine section having a vaned high pressure part and a low pressure part, said low pressure part comprising a shaft for driving said compressor, said high pressure part driving a power transmitting shaft; a system of pivotally mounted inlet guide vanes for controlling the angle of deflection of the gases from the combustion section relative to the vanes of said high pressure part; a servomotor for actuating said inlet guide vanes; an adjustable fuel valve for said combustion section; regulating means for said fuel valve and for said servomotor; one of said regulating means being adapted to be controlled from a reference value means for the desired power transmission; tachometer means connected to said low pressure part, said tachometer means being effective to control the other of said regulating means.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)
US00209120A 1971-02-01 1971-12-17 Gas turbine equipment and method of controlling such equipment Expired - Lifetime US3765169A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
SE01175/71A SE349630B (enrdf_load_stackoverflow) 1971-02-01 1971-02-01

Publications (1)

Publication Number Publication Date
US3765169A true US3765169A (en) 1973-10-16

Family

ID=20257720

Family Applications (1)

Application Number Title Priority Date Filing Date
US00209120A Expired - Lifetime US3765169A (en) 1971-02-01 1971-12-17 Gas turbine equipment and method of controlling such equipment

Country Status (5)

Country Link
US (1) US3765169A (enrdf_load_stackoverflow)
CH (1) CH541718A (enrdf_load_stackoverflow)
DE (1) DE2163846A1 (enrdf_load_stackoverflow)
FR (1) FR2124253B1 (enrdf_load_stackoverflow)
SE (1) SE349630B (enrdf_load_stackoverflow)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6725643B1 (en) * 2001-06-19 2004-04-27 Marius Paul High efficiency gas turbine power generator systems
US6751940B1 (en) * 2001-05-08 2004-06-22 Marius Paul High efficiency gas turbine power generator

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
SE404948B (sv) * 1977-03-25 1978-11-06 Stal Laval Turbin Ab Tvaaxlig gasturbinanleggning
US5193337A (en) * 1988-07-25 1993-03-16 Abb Stal Ab Method for operating gas turbine unit for combined production of electricity and heat
CA1298615C (en) * 1988-07-25 1992-04-07 Henrik Harboe Gas turbine unit for combined production of electricity and heat and method for operating such unit

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1126906A (fr) * 1951-08-08 1956-12-04 Turbine à gaz, plus spécialement pour véhicules
US3325994A (en) * 1964-12-11 1967-06-20 Bbc Brown Boveri & Cie Apparatus for regulating fuel and motive fluid flow in a gas turbine engine
US3508395A (en) * 1968-04-01 1970-04-28 Ford Motor Co Control system for motor vehicle type gas turbine engine
US3621657A (en) * 1968-09-25 1971-11-23 Daimler Benz Ag Control installation for the automatic adjustment of the movable guide blades especially of the output turbine of a gas turbine drive unit
US3686860A (en) * 1970-09-25 1972-08-29 Chandler Evans Inc Nozzle control

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3168810A (en) * 1962-08-29 1965-02-09 Gen Electric Two shaft gas turbine control system
FR2040911A5 (enrdf_load_stackoverflow) * 1969-04-16 1971-01-22 Chandler Evans Inc

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1126906A (fr) * 1951-08-08 1956-12-04 Turbine à gaz, plus spécialement pour véhicules
US3325994A (en) * 1964-12-11 1967-06-20 Bbc Brown Boveri & Cie Apparatus for regulating fuel and motive fluid flow in a gas turbine engine
US3508395A (en) * 1968-04-01 1970-04-28 Ford Motor Co Control system for motor vehicle type gas turbine engine
US3621657A (en) * 1968-09-25 1971-11-23 Daimler Benz Ag Control installation for the automatic adjustment of the movable guide blades especially of the output turbine of a gas turbine drive unit
US3686860A (en) * 1970-09-25 1972-08-29 Chandler Evans Inc Nozzle control

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6751940B1 (en) * 2001-05-08 2004-06-22 Marius Paul High efficiency gas turbine power generator
US6725643B1 (en) * 2001-06-19 2004-04-27 Marius Paul High efficiency gas turbine power generator systems

Also Published As

Publication number Publication date
CH541718A (de) 1973-09-15
FR2124253A1 (enrdf_load_stackoverflow) 1972-09-22
DE2163846A1 (de) 1972-08-10
SE349630B (enrdf_load_stackoverflow) 1972-10-02
FR2124253B1 (enrdf_load_stackoverflow) 1976-10-29

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