GB742477A - Improvements in or relating to bladed stator or rotor constructions for fluid machines such as axial-flow turbines or compressors - Google Patents

Improvements in or relating to bladed stator or rotor constructions for fluid machines such as axial-flow turbines or compressors

Info

Publication number
GB742477A
GB742477A GB27512/52A GB2751252A GB742477A GB 742477 A GB742477 A GB 742477A GB 27512/52 A GB27512/52 A GB 27512/52A GB 2751252 A GB2751252 A GB 2751252A GB 742477 A GB742477 A GB 742477A
Authority
GB
United Kingdom
Prior art keywords
passages
blade
passage
adjacent
shrouding
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
GB27512/52A
Inventor
Adrian Albert Lombard
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Publication of GB742477A publication Critical patent/GB742477A/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
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • 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
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • 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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/205—Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes

Landscapes

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

Abstract

742,477. Turbines and compressors. ROLLS-ROYCE. Ltd. Oct. 23, 1953 [Oct. 31, 1952], No. 27512/52. Class 110(3) In a bladed rotor or stator assembly for an axial-flow turbine or compressor, the blades each have at least one longitudinal passage formed therein adjacent the leading edge, a second longitudinal passage adjacent the trailing edge and a third longitudinal passage adjacent the midchord of the blade, the passages being interconnected at one end of the blade. The ends of the first and second passages remote from the interconnection are fed with fluid under pressure for cooling or heating purposes, the fluid being discharged from the blade through the end of the third passage which is remote from the interconnection. The fluid in the case of blades of a turbine in a gas turbine engine may be cooling air taken from the engine compressor. A turbine rotor blade is shown in Figs. 1, 2, and comprises a vane portion 11 formed with passages 17, 18 adjacent the leading and trailing edges and a larger passage 19 at the mid-chord. The passages are interconnected at 22 adiacent the blade tip and cooling air is fed upwardly through passages 17, 18 and downwardly through passage 19. The blade is mounted in rotors as described in Specification 742,476. The invention is shown applied to inlet nozzle guide vanes of a gas turbine in. Fig, 11. The vane 60 has three passages 63, 64, 65 and is mounted in inner and outer shrouding structures 61, 62 which are in the form of annular manifolds. The inner shrouding comprises two channel-shaped members 66, 70 which form an inlet manifold 87 therebetween and the outer shrouding also comprises two channel-shaped members 77, 78 which form an interconnecting manifold 83. The channel member 70 of the inner shrouding is formed with depressions 73 which are disposed opposite the inner end of each vane 60, the depressions having ports therein which register with the discharge passages 65. Cooling air is supplied through the pipe 75 and after passing through the blade discharges from the passage 65 into the working fluid stream. The inner and outer shrouds are located in stator structure 76, 86 by means of dogs 69, 85 respectively. In Fig. 13, the blade is formed with a number of small passages 90, 91 adjacent the leading and trailing edges and a single large passage 92 of the' mid-chord. Specification 699,582 also is referred to.
GB27512/52A 1952-10-31 1952-10-31 Improvements in or relating to bladed stator or rotor constructions for fluid machines such as axial-flow turbines or compressors Expired GB742477A (en)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
GB318289X 1952-10-31
GB318290X 1952-10-31
GB325000X 1953-05-15
GB231053X 1953-10-23

Publications (1)

Publication Number Publication Date
GB742477A true GB742477A (en) 1955-12-30

Family

ID=27448583

Family Applications (1)

Application Number Title Priority Date Filing Date
GB27512/52A Expired GB742477A (en) 1952-10-31 1952-10-31 Improvements in or relating to bladed stator or rotor constructions for fluid machines such as axial-flow turbines or compressors

Country Status (3)

Country Link
CH (1) CH318290A (en)
FR (1) FR1090194A (en)
GB (1) GB742477A (en)

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1039535B (en) * 1956-02-03 1958-09-25 Napier & Son Ltd Device for vibration damping of hot steam or hot gas turbine blades or compressor blades
DE1069153B (en) * 1956-03-14 1959-11-19 D. Naoier S. Son Limited, London Hollow blades for turbines or compressors
US3044745A (en) * 1956-11-20 1962-07-17 Rolls Royce Turbine and compressor blades
US3051439A (en) * 1958-06-18 1962-08-28 Rolls Royce Blades for gas turbine engines
DE1212108B (en) * 1962-07-11 1966-03-10 Gen Electric Single-edged axial flow machine impeller
US3574482A (en) * 1969-01-23 1971-04-13 Gen Electric Turbomachinery blades
US4462754A (en) * 1981-06-30 1984-07-31 Rolls Royce Limited Turbine blade for gas turbine engine
GB2250548A (en) * 1990-12-06 1992-06-10 Rolls Royce Plc Cooled turbine aerofoil blade
GB2319308A (en) * 1996-11-12 1998-05-20 Rolls Royce Plc Cooling gas turbine blades
WO1999047792A1 (en) * 1998-03-16 1999-09-23 Siemens Westinghouse Power Corporation Turbine blade assembly with cooling air handling device
EP1013882A3 (en) * 1998-12-24 2001-12-05 Rolls-Royce Plc Gas turbine engine internal air system
EP1249578A1 (en) * 2001-04-11 2002-10-16 Siemens Aktiengesellschaft Cooling of a gas turbine
CN106224011A (en) * 2015-05-01 2016-12-14 通用电气公司 Turbine dovetail groove heat shield
GB2569695A (en) * 2016-09-02 2019-06-26 Rolls Royce Plc Gas turbine engine
CN112673149A (en) * 2018-08-21 2021-04-16 西门子能源全球两合公司 Modular casing manifold for cooling fluid of gas turbine engine

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2920866A (en) * 1954-12-20 1960-01-12 A V Roe Canada Ltd Hollow air cooled sheet metal turbine blade
US2945671A (en) * 1955-02-10 1960-07-19 Rolls Royce Bladed rotor constructions for fluid machines
BE551145A (en) * 1955-09-26
FR1155958A (en) * 1956-03-28 1958-05-12 Improvements to compressible fluid turbines
FR2468727A1 (en) * 1979-10-26 1981-05-08 Snecma IMPROVEMENT TO COOLED TURBINE AUBES
FR2858352B1 (en) * 2003-08-01 2006-01-20 Snecma Moteurs COOLING CIRCUIT FOR TURBINE BLADE

Cited By (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1039535B (en) * 1956-02-03 1958-09-25 Napier & Son Ltd Device for vibration damping of hot steam or hot gas turbine blades or compressor blades
DE1069153B (en) * 1956-03-14 1959-11-19 D. Naoier S. Son Limited, London Hollow blades for turbines or compressors
US3044745A (en) * 1956-11-20 1962-07-17 Rolls Royce Turbine and compressor blades
US3051439A (en) * 1958-06-18 1962-08-28 Rolls Royce Blades for gas turbine engines
DE1212108B (en) * 1962-07-11 1966-03-10 Gen Electric Single-edged axial flow machine impeller
US3574482A (en) * 1969-01-23 1971-04-13 Gen Electric Turbomachinery blades
US4462754A (en) * 1981-06-30 1984-07-31 Rolls Royce Limited Turbine blade for gas turbine engine
GB2250548A (en) * 1990-12-06 1992-06-10 Rolls Royce Plc Cooled turbine aerofoil blade
GB2319308B (en) * 1996-11-12 2001-02-28 Rolls Royce Plc Gas turbine engine turbine system
GB2319308A (en) * 1996-11-12 1998-05-20 Rolls Royce Plc Cooling gas turbine blades
US5941687A (en) * 1996-11-12 1999-08-24 Rolls-Royce Plc Gas turbine engine turbine system
WO1999047792A1 (en) * 1998-03-16 1999-09-23 Siemens Westinghouse Power Corporation Turbine blade assembly with cooling air handling device
US6059529A (en) * 1998-03-16 2000-05-09 Siemens Westinghouse Power Corporation Turbine blade assembly with cooling air handling device
EP1013882A3 (en) * 1998-12-24 2001-12-05 Rolls-Royce Plc Gas turbine engine internal air system
EP1249578A1 (en) * 2001-04-11 2002-10-16 Siemens Aktiengesellschaft Cooling of a gas turbine
US6702547B2 (en) 2001-04-11 2004-03-09 Siemens Aktiengesellschaft Gas turbine
CN106224011A (en) * 2015-05-01 2016-12-14 通用电气公司 Turbine dovetail groove heat shield
US10094228B2 (en) 2015-05-01 2018-10-09 General Electric Company Turbine dovetail slot heat shield
CN106224011B (en) * 2015-05-01 2019-02-19 通用电气公司 Turbine dovetail groove heat shield
GB2569695A (en) * 2016-09-02 2019-06-26 Rolls Royce Plc Gas turbine engine
CN112673149A (en) * 2018-08-21 2021-04-16 西门子能源全球两合公司 Modular casing manifold for cooling fluid of gas turbine engine

Also Published As

Publication number Publication date
CH318290A (en) 1956-12-31
FR1090194A (en) 1955-03-28

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