EP0496571A1 - Turbine à gaz - Google Patents

Turbine à gaz Download PDF

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Publication number
EP0496571A1
EP0496571A1 EP92300492A EP92300492A EP0496571A1 EP 0496571 A1 EP0496571 A1 EP 0496571A1 EP 92300492 A EP92300492 A EP 92300492A EP 92300492 A EP92300492 A EP 92300492A EP 0496571 A1 EP0496571 A1 EP 0496571A1
Authority
EP
European Patent Office
Prior art keywords
gas
nozzles
turbine
blades
annular
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.)
Withdrawn
Application number
EP92300492A
Other languages
German (de)
English (en)
Inventor
Ronald George Cook
Alan Ernest Massey
Geoffrey Edward Bone
Nicholas Black
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.)
GEC AEROSPACE Ltd
Original Assignee
GEC AEROSPACE Ltd
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 GEC AEROSPACE Ltd filed Critical GEC AEROSPACE Ltd
Publication of EP0496571A1 publication Critical patent/EP0496571A1/fr
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
    • F01D1/02—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines
    • F01D1/023—Non-positive-displacement machines or engines, e.g. steam turbines with stationary working-fluid guiding means and bladed or like rotor, e.g. multi-bladed impulse steam turbines the working-fluid being divided into several separate flows ; several separate fluid flows being united in a single flow; the machine or engine having provision for two or more different possible fluid flow paths
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/141—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/18—Final actuators arranged in stator parts varying effective number of nozzles or guide conduits, e.g. sequentially operable valves for steam turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/50—Application for auxiliary power units (APU's)
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/40—Movement of components
    • F05D2250/41—Movement of components with one degree of freedom
    • F05D2250/411—Movement of components with one degree of freedom in rotation

Definitions

  • This invention relates to gas turbines and is especially applicable to gas turbines for use as an auxiliary power unit on aircraft.
  • gas turbines on an aircraft to drive,a hydraulic pump or to supply on-demand or continuous power
  • a typical use of such a gas turbine would be on a four-engined, long-haul jet aircraft in which one or more gas turbines would operate, for example, from engine bleed air.
  • the efficiency of the gas turbine has not been particularly important because of the large amount of bleed air which is available.
  • a gas turbine comprising a turbine wheel having a plurality of outwardly extending blades, a first set of nozzles for directing gas to at least some of said blades and a second set of nozzles for directing gas to at least some of said blades, a gas inlet, a first gas duct extending from said gas inlet for directing gas to said first set of nozzles and a second gas duct extending from said gas inlet for directing gas to said second set of nozzles, said first and second gas ducts each being of annular form, parts of each of which are disposed concentrically, and gas flow control means for controlling the gas flows in said first and second gas ducts, said gas flow control means being disposed centrally within said first and second annular gas ducts, said first and second annular gas ducts having openings which are at least partially closeable by said gas flow control means for controlling the gas flows therein.
  • first set of nozzles are disposed in said first annular gas duct and said second set of nozzles are disposed in said second annular gas duct.
  • said turbine wheel comprises a first set of outwardly extending blades to which said first set of nozzles direct gas, and a second set of outwardly extending blades to which said second set of nozzles direct gas, said first set of blades being disposed radially outwards of said second set of blades.
  • said first and second sets of blades are separated by a cylindrical separator.
  • the opening of said first duct is disposed upstream of the opening of said second duct, said gas flow control means being disposed downstream of the openings of said first and second ducts, and being moveable to selectively close said openings.
  • said gas flow control means comprises a differential pressure piston actuator.
  • the said first set of nozzles and said first set of outwardly extending blades on said turbine wheel are designed for low pressure gas supply operation and the said second set of nozzles and said second set of outwardly extending blades on said turbine wheel are designed for high pressure gas supply operation, whereby high efficiency operation at said low pressure and at said high pressure is achieved.
  • the gas turbine shown in the drawing comprises a generally cylindrical turbine housing 1 having a reduced diameter gas/bleed air inlet 2, the gas or bleed air input to which is used to drive a turbine wheel 3.
  • the turbine wheel 3 is mounted on a shaft 4 which may constitute part of a reduction gear-box (not shown) which itself may be used to drive a hydraulic pump (not shown) or other auxiliary equipment in well known manner.
  • the turbine housing 1 is provided with an outer (high pressure-HP) annular duct 5 disposed between the housing 1 and an intermediate shroud 6 and an inner (low pressure - LP) annular duct 7 disposed between the intermediate shroud 6 and a generally cylindrical inner shroud 8.
  • the HP and LP annular ducts 5 and 7 respectively have circumferential openings 9 and 10 respectively, disposed adjacent to one another in the inner shroud 8 and adjacent to the inlet 2, the opening 10 to the LP annular duct 7 being downstream of the HP annular duct 5.
  • the intermediate shroud 6 is held in spaced relationship from the housing 1 by means of radially disposed spacer plates 11 and the inner shroud 8 is held in spaced relationship from the intermediate shroud 6 by means of radially disposed spacer plates 12.
  • control valve 13 having a generally pointed front end 14, the control valve 13 being axially movable in the inner shroud 8 under the control of a differential pressure piston actuator 15 in order to control the flow of gas/bleed air from the inlet 2 to the openings 9 and 10 of the HP and LP annular ducts 5 and 7.
  • the control valve 13 is shown in the drawings in a position corresponding to a LP condition (Design Point 1) in which gas/bleed air from the inlet 2 is directed through the openings 9 and 10 of the HP and LP annular ducts 5 and 7.
  • the control valve 13 is axially movable in the inner shroud 8 under the control of the differential piston actuator 15 towards the inlet 2 to a position 16 shown in dashed outline which corresponds to a HP condition (Design Point 2) in which the opening 10 of the LP annular duct 7 is virtually closed by the control valve 13, and gas/bleed air from the inlet 2 is directed mainly through the opening 9 of the HP annular duct 5.
  • control valve 13 is movable towards the inlet 2 to a position 17 shown in dashed outline in which the opening 9 of the HP annular duct 5 is virtually closed to regulate the flow of gas/bleed air to the HP annular duct 5.
  • the turbine wheel 3 consists of a circular inner portion 22 from which the set of LP turbine blades 21 radially extend to an intermediate cylindrical separator 23, which aligns with the intermediate shroud 6 between the annular ducts 5 and 7, so that the LP turbine blades 21 align with the LP nozzles 19.
  • the HP turbine blades 20 extend from the separator 23 to the outer periphery of the turbine wheel 3 and align with the HP nozzles 18.
  • Exhaust gas/bleed air from the turbine blades 20 and 21 are directed to an exhaust duct 24 which is advantageously tailored to afford a jet pump effect from the gas/bleed air from the HP turbine blades 20.
  • the gas turbine which has been described has the capacity to drive a peak load at constant speed and to have a high efficiency when operating on (a) low pressure-LP (Design Point 1) and (b) high pressure (Design Point 2). Intermediate gas/bleed air supply conditions are, considered less important in terms of efficiency. This is achieved by tailoring the LP annular duct 7, the LP nozzles 19 and the LP turbine blades 21, such that when the control valve 13 is in the position shown in full lines in the drawings, i.e.
  • the required efficiency at low pressure - Design Point 1 is obtained, and by tailoring the HP annular duct 5, the HP nozzles 18 and the HP turbine blades 20, such that when the control valve 13 is in the position 16 shown in dashed lines in Fig. 1, i.e. with the opening 10 to the LP annular duct 7 closed, the required efficiency at high pressure-Design Point 2 is obtained.
  • Control of the speed of the turbine wheel 3 is effected by adjusting the axial movement of the control valve 13. This is achieved by means of the differential pressure piston actuator 15, one side of which is subjected to the pressure of the gas/bleed air supply and the other side of which is subjected to a modulated pressure signal which is derived from a pressure outlet 25 which is upstream of the control valve 13 and which is adjusted in accordance with the speed of the turbine wheel and is applied to a pressure inlet 26 which couples to the differential piston actuator 15.
  • control valve 13 At the low pressure Design Point 1, the control valve 13 is positioned such that the opening 10 to the LP annular duct 7 is almost fully open, permitting a minimum amount of throttling of the control valve 13 to maintaining constant turbine speed at peak turbine load. Under these conditions a small amount of flow takes place in the HP annular duct 5.
  • the control valve 13 is positioned such that the opening 10 to the LP annular duct 7 is fully closed, although a small amount of controlled leakage to the LP nozzles 19 may be permitted to minimise losses, and the opening 9 to the HP annular duct 5 is almost fully open permitting a minimum amount of throttling of the control valve 13 to maintain constant turbine speed at peak turbine load.
  • control valve 13 Under conditions where supply pressure exceeds the HP Design Point 2, the control valve 13 causes the opening 9 to the HP annular duct 5 to be progressively closed, permitting additional throttling of the control valve 13 to maintain constant turbine speed at lower efficiency.
  • gas turbine which has been described has been given by way of example only and may be modified to suit any particular application.
  • two annular ducts 5, 7 with corresponding fixed nozzles 18, 19 and turbine blades 20, 21 have been described, it is envisaged that more than two annular ducts could be used.
  • the turbine wheel 3 is provided with two sets of turbine blades 20, 21 it is envisaged that a single set of turbine blades could be provided corresponding to the fixed nozzles 18, 19. It is also possible where, for instance, a low reaction is employed, to eliminate the separator 23 of the turbine wheel 3.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Control Of Turbines (AREA)
EP92300492A 1991-01-25 1992-01-21 Turbine à gaz Withdrawn EP0496571A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB9101719 1991-01-25
GB9101719A GB2252133A (en) 1991-01-25 1991-01-25 Gas turbines

Publications (1)

Publication Number Publication Date
EP0496571A1 true EP0496571A1 (fr) 1992-07-29

Family

ID=10689050

Family Applications (1)

Application Number Title Priority Date Filing Date
EP92300492A Withdrawn EP0496571A1 (fr) 1991-01-25 1992-01-21 Turbine à gaz

Country Status (2)

Country Link
EP (1) EP0496571A1 (fr)
GB (1) GB2252133A (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10041407B2 (en) 2011-03-29 2018-08-07 General Electric Company System and method for air extraction from gas turbine engines

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1155172A (fr) * 1956-07-05 1958-04-23 Plessey Co Ltd Turbine à air ou à gaz
FR1194802A (fr) * 1958-04-17 1959-11-12 Rateau Et Rene Anxionnaz Soc Perfectionnement aux turbines à gaz
DE2840201A1 (de) * 1978-09-15 1980-03-27 Maschf Augsburg Nuernberg Ag Vorrichtung zur veraenderung der zustroemquerschnittsflaeche der turbine eines abgasturboladers
EP0191380A1 (fr) * 1985-02-20 1986-08-20 BBC Brown Boveri AG Turbine pour une turbosoufflante

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB428355A (en) * 1934-01-09 1935-05-10 Fried Krupp Germaniawerft Ag Improvements in or relating to turbine plants
GB569579A (en) * 1942-11-09 1945-05-30 Goetaverken Ab Improvements in turbines
GB801317A (en) * 1955-06-08 1958-09-10 Vickers Armstrongs Ltd Improvements in or relating to turbine control valves
US3802797A (en) * 1973-01-15 1974-04-09 Gen Electric Reversing turbine flow divider support
DE2633587C2 (de) * 1976-07-27 1985-05-23 Klöckner-Humboldt-Deutz AG, 5000 Köln Abgasturbolader für eine Brennkraftmaschine
EP0180917A3 (fr) * 1984-11-02 1987-09-16 Hitachi, Ltd. Suralimentateur de type turbine à gaz d'échappement

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1155172A (fr) * 1956-07-05 1958-04-23 Plessey Co Ltd Turbine à air ou à gaz
FR1194802A (fr) * 1958-04-17 1959-11-12 Rateau Et Rene Anxionnaz Soc Perfectionnement aux turbines à gaz
DE2840201A1 (de) * 1978-09-15 1980-03-27 Maschf Augsburg Nuernberg Ag Vorrichtung zur veraenderung der zustroemquerschnittsflaeche der turbine eines abgasturboladers
EP0191380A1 (fr) * 1985-02-20 1986-08-20 BBC Brown Boveri AG Turbine pour une turbosoufflante

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10041407B2 (en) 2011-03-29 2018-08-07 General Electric Company System and method for air extraction from gas turbine engines

Also Published As

Publication number Publication date
GB9101719D0 (en) 1991-03-06
GB2252133A (en) 1992-07-29

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