GB836952A - Improvements in cooling means for a multi-stage turbine - Google Patents

Improvements in cooling means for a multi-stage turbine

Info

Publication number
GB836952A
GB836952A GB3251/58A GB325158A GB836952A GB 836952 A GB836952 A GB 836952A GB 3251/58 A GB3251/58 A GB 3251/58A GB 325158 A GB325158 A GB 325158A GB 836952 A GB836952 A GB 836952A
Authority
GB
United Kingdom
Prior art keywords
discs
rotor discs
disc
shaft
rotor
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
GB3251/58A
Inventor
Joseph Savage Alford
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Priority to GB3251/58A priority Critical patent/GB836952A/en
Publication of GB836952A publication Critical patent/GB836952A/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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Abstract

836,952. Cooling turbine rotors. GENERAL ELECTRIC CO. Jan. 31, 1958, No. 3251/58. Class 110 (3). A multi-stage turbine comprises at least two rotor discs carried by a shaft member, the rotor discs being interconnected at their peripheries by a spacer ring, a disc member being disposed between the rotor discs and carrying radially- and axially-extending vanes, coolant fluid being introduced into the space between adjacent rotor discs at one side of the vane-supporting disc and withdrawn at the other side. The turbine shown comprises three discs 12, the two upstream discs being mounted on shaft 10 for rotation therewith. The two downstream discs are interconnected adjacent their inner peripheries by a ring member 25 secured to the discs. A core member 11 is supported within the shaft 10 and ring 25 by means of baffle members 14. The rotor discs 12 are interconnected adjacent their outer peripheries by spacer rings 16. Disc members 21 are supported in the spaces between adjacent rotor discs 12, each disc having four radially- and axially-extending vanes 22 secured at its upstream side and similar vanes 28 secured at its downstream side. Cooling fluid such as air from a compressor is supplied through hollow shaft 10 and enters the space between the first two rotor discs through ports 19 in shaft 10 and discharges therefrom through ports 20, the flow of cooling air in the space being as indicated by arrows. The cooling fluid then enters the space between the second and third rotor discs through ports 26 in the ring member 25 and discharges therefrom through ports 29. The inner faces of the spacer rings 16 are formed with axially-extending fins 27, and the outer surfaces with circumferentially-extending ribs 18 which with stator parts form labyrinth seals. The vanes 22 are connected to the first stage rotor disc 12 by links 24.
GB3251/58A 1958-01-31 1958-01-31 Improvements in cooling means for a multi-stage turbine Expired GB836952A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB3251/58A GB836952A (en) 1958-01-31 1958-01-31 Improvements in cooling means for a multi-stage turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB3251/58A GB836952A (en) 1958-01-31 1958-01-31 Improvements in cooling means for a multi-stage turbine

Publications (1)

Publication Number Publication Date
GB836952A true GB836952A (en) 1960-06-09

Family

ID=9754809

Family Applications (1)

Application Number Title Priority Date Filing Date
GB3251/58A Expired GB836952A (en) 1958-01-31 1958-01-31 Improvements in cooling means for a multi-stage turbine

Country Status (1)

Country Link
GB (1) GB836952A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2782539A1 (en) * 1998-08-20 2000-02-25 Snecma Compressor for gas turbine engine has cooling cavity contained within rotor and cooling surface formed in part by part of outer wall of rotor
EP3508688A1 (en) * 2018-01-08 2019-07-10 United Technologies Corporation Gas turbine engine and compressor
WO2019197750A1 (en) 2018-04-13 2019-10-17 Safran Aircraft Engines Turbomachine comprising a device for improving the cooling of rotor discs by an air flow
CN113250754A (en) * 2021-04-22 2021-08-13 中国民用航空飞行学院 Flow structure for counter-rotating disc cavity

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2782539A1 (en) * 1998-08-20 2000-02-25 Snecma Compressor for gas turbine engine has cooling cavity contained within rotor and cooling surface formed in part by part of outer wall of rotor
EP1120544A1 (en) * 1998-08-20 2001-08-01 Snecma Moteurs Turbo machine with a device for supplying a pressurized gas
US6334755B1 (en) 1998-08-20 2002-01-01 Snecma Moteurs Turbomachine including a device for supplying pressurized gas
EP3508688A1 (en) * 2018-01-08 2019-07-10 United Technologies Corporation Gas turbine engine and compressor
US10767485B2 (en) 2018-01-08 2020-09-08 Raytheon Technologies Corporation Radial cooling system for gas turbine engine compressors
WO2019197750A1 (en) 2018-04-13 2019-10-17 Safran Aircraft Engines Turbomachine comprising a device for improving the cooling of rotor discs by an air flow
FR3080150A1 (en) * 2018-04-13 2019-10-18 Safran Aircraft Engines TURBOMACHINE COMPRISING A DEVICE FOR ENHANCING THE COOLING OF ROTOR DISCS BY AN AIR FLOW
CN113250754A (en) * 2021-04-22 2021-08-13 中国民用航空飞行学院 Flow structure for counter-rotating disc cavity
CN113250754B (en) * 2021-04-22 2023-05-05 中国民用航空飞行学院 Flow structure for turntable cavity

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