[go: up one dir, main page]
More Web Proxy on the site http://driver.im/

GB853314A - Improvements in or relating to axial flow turbo-machines such as turbines or compressors - Google Patents

Improvements in or relating to axial flow turbo-machines such as turbines or compressors

Info

Publication number
GB853314A
GB853314A GB3050756A GB3050756A GB853314A GB 853314 A GB853314 A GB 853314A GB 3050756 A GB3050756 A GB 3050756A GB 3050756 A GB3050756 A GB 3050756A GB 853314 A GB853314 A GB 853314A
Authority
GB
United Kingdom
Prior art keywords
extensions
blade
extension
blades
members
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
GB3050756A
Inventor
Neil Milligan Clark
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.)
Power Jets Research and Development Ltd
Original Assignee
Power Jets Research and Development 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 Power Jets Research and Development Ltd filed Critical Power Jets Research and Development Ltd
Priority to GB3050756A priority Critical patent/GB853314A/en
Priority to FR1183012D priority patent/FR1183012A/en
Publication of GB853314A publication Critical patent/GB853314A/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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/02—Preventing or minimising internal leakage of working-fluid, e.g. between stages by non-contact sealings, e.g. of labyrinth type
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

853,314. Turbine and compressor blades. POWER JETS (RESEARCH & DEVELOPMENT) Ltd. Aug. 30, 1957 [Oct. 5, 1956], No. 30507/56. Class 110 (3). In an axial-flow turbine or compressor having shrouded blades, each blade has an extension or extensions which projects or project beyond the shroud in a direction away from the working portion of the blade, the extension or extensions carrying two segmental blocks, at least one of which has sealing means arranged to co-operate with a part of the machine with which the blades are relatively rotatable, the segmental blocks and the blade extension or extensions being shaped to interlock. In a first embodiment, the blades 1 are of aerofoil profile and have root portions 15, the opposite ends of the blades being formed with dovetailshaped extensions 2 which are passed through openings 4 in shroud members 3, the shrouds abutting against shoulders formed on the blades. Pairs of segmental members 5, 6 are clamped by means of bolts 8 to the blade extensions 2, the members 5, 6 having grooves which together correspond to the dovetail shape of the extensions 2. The members 5, 6 are provided with fins 7 which co-operate with the adjacent surface of the rotor to provide a seal. A plurality of parts 5, 6 are provided so as to afford a substantially continuous ring member.. In Fig. 4 the blade tip is shaped to provide a dovetail-shaped groove 12, the blade tip being passed through an opening in a shroud member 9. Two wedge-shaped members 10 are held against the sides of the groove 12 by means of a wedge-shaped key member 14 which is urged towards the bottom of the groove 12 by means of a bolt 13 engaging with the shroud 9. Sealing fins 11 are provided on the wedge members 10. In Fig. 5, the blade is formed integral with a shroud 18 and dovetail-shaped extension 19, pairs of segmental parts 20 which are grooved to correspond to the dovetail extension 19 being clamped to the extension by screws 21. Sealing fins 22 are provided on the segmental parts 20.
GB3050756A 1956-10-05 1956-10-05 Improvements in or relating to axial flow turbo-machines such as turbines or compressors Expired GB853314A (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
GB3050756A GB853314A (en) 1956-10-05 1956-10-05 Improvements in or relating to axial flow turbo-machines such as turbines or compressors
FR1183012D FR1183012A (en) 1956-10-05 1957-10-02 Improvements to axial turbo-machines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB3050756A GB853314A (en) 1956-10-05 1956-10-05 Improvements in or relating to axial flow turbo-machines such as turbines or compressors

Publications (1)

Publication Number Publication Date
GB853314A true GB853314A (en) 1960-11-02

Family

ID=10308766

Family Applications (1)

Application Number Title Priority Date Filing Date
GB3050756A Expired GB853314A (en) 1956-10-05 1956-10-05 Improvements in or relating to axial flow turbo-machines such as turbines or compressors

Country Status (2)

Country Link
FR (1) FR1183012A (en)
GB (1) GB853314A (en)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3079128A (en) * 1961-01-23 1963-02-26 Burge Joseph Sealing and securing means for turbomachine blading
US4884820A (en) * 1987-05-19 1989-12-05 Union Carbide Corporation Wear resistant, abrasive laser-engraved ceramic or metallic carbide surfaces for rotary labyrinth seal members
US4889470A (en) * 1988-08-01 1989-12-26 Westinghouse Electric Corp. Compressor diaphragm assembly
DE102009042029A1 (en) * 2009-09-17 2011-03-24 Mtu Aero Engines Gmbh Blade ring for flow machine, particularly for gas turbine, has hardened reinforcement on inner shroud, where reinforcement is closed in circumferential direction
CN110761848A (en) * 2019-12-16 2020-02-07 中国船舶重工集团公司第七0三研究所 Gas compressor stator blade ring of gas turbine
DE102018213983A1 (en) * 2018-08-20 2020-02-20 MTU Aero Engines AG Adjustable guide vane arrangement, guide vane, seal carrier and turbomachine
CN112324520A (en) * 2020-10-27 2021-02-05 中国船舶重工集团公司第七0三研究所 Stationary blade ring structure of gas turbine

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4834613A (en) * 1988-02-26 1989-05-30 United Technologies Corporation Radially constrained variable vane shroud
US7329096B2 (en) * 2005-10-18 2008-02-12 General Electric Company Machine tooled diaphragm partitions and nozzles

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3079128A (en) * 1961-01-23 1963-02-26 Burge Joseph Sealing and securing means for turbomachine blading
US4884820A (en) * 1987-05-19 1989-12-05 Union Carbide Corporation Wear resistant, abrasive laser-engraved ceramic or metallic carbide surfaces for rotary labyrinth seal members
US4889470A (en) * 1988-08-01 1989-12-26 Westinghouse Electric Corp. Compressor diaphragm assembly
DE102009042029A1 (en) * 2009-09-17 2011-03-24 Mtu Aero Engines Gmbh Blade ring for flow machine, particularly for gas turbine, has hardened reinforcement on inner shroud, where reinforcement is closed in circumferential direction
DE102018213983A1 (en) * 2018-08-20 2020-02-20 MTU Aero Engines AG Adjustable guide vane arrangement, guide vane, seal carrier and turbomachine
US11300004B2 (en) 2018-08-20 2022-04-12 MTU Aero Engines AG Adjustable guide vane arrangement, guide vane, seal carrier and turbomachine
CN110761848A (en) * 2019-12-16 2020-02-07 中国船舶重工集团公司第七0三研究所 Gas compressor stator blade ring of gas turbine
CN112324520A (en) * 2020-10-27 2021-02-05 中国船舶重工集团公司第七0三研究所 Stationary blade ring structure of gas turbine
CN112324520B (en) * 2020-10-27 2022-08-30 中国船舶重工集团公司第七0三研究所 Stationary blade ring structure of gas turbine

Also Published As

Publication number Publication date
FR1183012A (en) 1959-07-02

Similar Documents

Publication Publication Date Title
US2920865A (en) Bladed stator or rotor constructions with means to supply a fluid internally of the blades
GB1287223A (en) Improvements in or relating to turbine blading
GB1512882A (en) Bladed rotor assembly for a gas turbine engine
GB1465282A (en) Leakage control structure
GB1272200A (en) Axial-flow turbomachine rotors
GB1505534A (en) Turbines and compressors
GB748912A (en) Improvements in or relating to blade assemblies of compressors and turbines and likemachines
GB1491556A (en) Rotor blades for turbomachines
GB1195012A (en) Rotor for Bladed Fluid Flow Machines.
GB853314A (en) Improvements in or relating to axial flow turbo-machines such as turbines or compressors
US3702222A (en) Rotor blade structure
GB1276100A (en) Bladed member for a fluid flow machine
GB1211188A (en) Gas turbine engines
GB980656A (en) Improvements in and relating to turbines and like machines
GB767656A (en) Improvements in or relating to axial-flow fluid machines such as turbines and compressors
GB1174170A (en) Elastic fluid turbine rot or cooling arrangement
GB748903A (en) Blades for compressors, turbines and like bladed rotary machines
GB1533556A (en) Turbo-machine rotor wheel
GB1148339A (en) Compressors or turbines for gas turbine engines
GB1141280A (en) Bladed rotor for a fluid flow machine
GB1406098A (en) Fluid flow machines
GB789733A (en) Improvements in or relating to structural elements for axial-flow compressors or turbines or the like machines
GB1527074A (en) Bladed rotors
GB1509185A (en) Fluid driven turbo machines
GB1013835A (en) Improvements in or relating to axial-flow turbines, compressors and exhausters