GB744548A - Improvements in or relating to gas turbines - Google Patents

Improvements in or relating to gas turbines

Info

Publication number
GB744548A
GB744548A GB2099653A GB2099653A GB744548A GB 744548 A GB744548 A GB 744548A GB 2099653 A GB2099653 A GB 2099653A GB 2099653 A GB2099653 A GB 2099653A GB 744548 A GB744548 A GB 744548A
Authority
GB
United Kingdom
Prior art keywords
cooling air
ring
chamber
flange
parts
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
GB2099653A
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.)
ARNOLD ROYDON BENNETT GAY
Bristol Siddeley Engines Ltd
Original Assignee
ARNOLD ROYDON BENNETT GAY
De Havilland Engine Co 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 ARNOLD ROYDON BENNETT GAY, De Havilland Engine Co Ltd filed Critical ARNOLD ROYDON BENNETT GAY
Priority to GB2099653A priority Critical patent/GB744548A/en
Publication of GB744548A publication Critical patent/GB744548A/en
Expired legal-status Critical Current

Links

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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

744,548. Gas turbine nozzle ring. DE HAVILLAND ENGINE CO.. Ltd.; HALFORD. F. B., and GAY, A. R. B. July 8, 1954 [July 29, 1953], No. 20996/53. Class 110(3) In an axial flow gas turbine, a nozzle ring assembly comprises a row of hollow guide vanes N mounted at the inner and outer ends in structure forming cooling air chambers a cooling air chamber also being formed around the turbine..rotor blades shroud ring. Cooling air is supplied to the chamber at the inner end of the guide vanes and flows through the vanes to the chamber at the outer end, the air then passing to the chamber surrounding the rotor shroud ring and finally escapes preferably into the gas stream leaving the rotor blade ring. The inner cooling air chamber E is formed by parts D, D1, B4, B5 which are bolted to a doublewalled structure B2, B3 through which cooling air is supplied. Distance pieces F1 are fitted between the parts D. B3 to provide passages for cooling air flow to the chamber E. The outer cooling air chamber is formed by parts J1, J, C2, C3, the parts C2, C3 being part of the turbine outer casing the deep flange part C3 being provided with apertures C1 in which the downstream ends of the combustion chambers A are received. The cooling air chamber T around the turbine rotor shroud ring P is formed by the casing M1 and flange M2 thereon and by the ring member I, and the shroud ring P. The ring member L and the flange M2 have inwardly-directed flanges H1 and M3 which receive the shroud ring P which is formed as a series of overlapping segments. Apertures S are formed in the ring members J and L to allow cooling air to enter the chamber T, the air finally escaping through apertures S1 in the flange M2 into the gas stream downstream of the rotor blades Q. Apertures U are formed in the flange B5 to allow cooling air to impinge near the rotor blade roots. The shroud ring P may alternatively be formed as a continuous ring. Each guide vane N is free in the parts D1, J1 and is located radially by a flange member O.
GB2099653A 1953-07-29 1953-07-29 Improvements in or relating to gas turbines Expired GB744548A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB2099653A GB744548A (en) 1953-07-29 1953-07-29 Improvements in or relating to gas turbines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB2099653A GB744548A (en) 1953-07-29 1953-07-29 Improvements in or relating to gas turbines

Publications (1)

Publication Number Publication Date
GB744548A true GB744548A (en) 1956-02-08

Family

ID=10155398

Family Applications (1)

Application Number Title Priority Date Filing Date
GB2099653A Expired GB744548A (en) 1953-07-29 1953-07-29 Improvements in or relating to gas turbines

Country Status (1)

Country Link
GB (1) GB744548A (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1220670B (en) * 1962-12-18 1966-07-07 Gen Electric Cooling device for gas turbine engines
GB2395756B (en) * 2002-11-27 2006-02-08 Rolls Royce Plc Cooled turbine assembly
EP2653659A3 (en) * 2012-04-19 2017-08-16 General Electric Company Cooling assembly for a gas turbine system
FR3048017A1 (en) * 2016-02-24 2017-08-25 Snecma AIRCRAFT TURBOMACHINE COMPRESSOR RECTIFIER, COMPRISING STRIPPED AIR-LIFTING ORIFICES ACCORDING TO THE CIRCUMFERENTIAL DIRECTION
DE102018206259A1 (en) * 2018-04-24 2019-10-24 MTU Aero Engines AG GUIDE SHOVEL FOR A TURBINE OF A FLOW MACHINE

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1220670B (en) * 1962-12-18 1966-07-07 Gen Electric Cooling device for gas turbine engines
GB2395756B (en) * 2002-11-27 2006-02-08 Rolls Royce Plc Cooled turbine assembly
EP2653659A3 (en) * 2012-04-19 2017-08-16 General Electric Company Cooling assembly for a gas turbine system
FR3048017A1 (en) * 2016-02-24 2017-08-25 Snecma AIRCRAFT TURBOMACHINE COMPRESSOR RECTIFIER, COMPRISING STRIPPED AIR-LIFTING ORIFICES ACCORDING TO THE CIRCUMFERENTIAL DIRECTION
WO2017144805A1 (en) * 2016-02-24 2017-08-31 Safran Aircraft Engines Rectifier for aircraft turbomachine compressor, comprising air extraction openings having a stretched form in the peripheral direction
CN108779682A (en) * 2016-02-24 2018-11-09 赛峰飞机发动机公司 It include the rectifier for aircraft turbine machine compressor that the air with the shape extended along circumferential direction extracts opening
CN108779682B (en) * 2016-02-24 2021-03-23 赛峰飞机发动机公司 Rectifier for aircraft turbomachine compressor comprising air extraction openings having a shape elongated in the circumferential direction
US11230936B2 (en) 2016-02-24 2022-01-25 Safran Aircraft Engines Rectifier for aircraft turbomachine compressor, comprising air extraction openings having a stretched form in the peripheral direction
DE102018206259A1 (en) * 2018-04-24 2019-10-24 MTU Aero Engines AG GUIDE SHOVEL FOR A TURBINE OF A FLOW MACHINE
EP3561236A1 (en) * 2018-04-24 2019-10-30 MTU Aero Engines GmbH Guide vane for a turbine of a turbomachine
US11215073B2 (en) 2018-04-24 2022-01-04 MTU Aero Engines AG Stator vane for a turbine of a turbomachine

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