GB938189A - Improvements in the construction of turbine and compressor blade elements - Google Patents

Improvements in the construction of turbine and compressor blade elements

Info

Publication number
GB938189A
GB938189A GB37254/60A GB3725460A GB938189A GB 938189 A GB938189 A GB 938189A GB 37254/60 A GB37254/60 A GB 37254/60A GB 3725460 A GB3725460 A GB 3725460A GB 938189 A GB938189 A GB 938189A
Authority
GB
United Kingdom
Prior art keywords
lugs
segments
blade
pairs
neighbouring
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
GB37254/60A
Inventor
John Alan Courtney Hyde
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.)
Ruston and Hornsby Ltd
Original Assignee
Ruston and Hornsby 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 Ruston and Hornsby Ltd filed Critical Ruston and Hornsby Ltd
Priority to GB37254/60A priority Critical patent/GB938189A/en
Priority to US144740A priority patent/US3182955A/en
Publication of GB938189A publication Critical patent/GB938189A/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
    • 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
    • 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
    • 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
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • 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
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • F05D2240/81—Cooled platforms
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y10T29/49321—Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member

Landscapes

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

Abstract

938,189. Turbines, elastic fluid. RUSTON & HORNSBY Ltd. Sept. 26, 1961 [Oct. 29, 1960], No. 37254/60. Class 110 (3). A blade segment for an axial flow compressor or turbine rotor or stator comprises at least one blade and either a shroud plate, a platform plate or both, the segments being connected together in an annular row by pairs of lugs spaced radially apart by grooves formed in the axially extending edges of the plates, the lugs on neighbouring segments being in contiguous relationship, the radially outer lugs of shrouds and inner lugs of platforms being butt welded to neighbouring lugs. Blade segments supported in a casing by brackets 22 are connected by pairs of lugs 14, 15 on the shroud 12 and platform 13. The lugs 15 are welded together. The lugs 14 may have cooperating flanges secured together as at 21. The grooves 16 between the lugs form channels 18 for cooling fluid which is passed through the blades 11 by passages 19, 20. The construction allows for thermal expansion and for individual segments to be cut out and replaced.
GB37254/60A 1960-10-29 1960-10-29 Improvements in the construction of turbine and compressor blade elements Expired GB938189A (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
GB37254/60A GB938189A (en) 1960-10-29 1960-10-29 Improvements in the construction of turbine and compressor blade elements
US144740A US3182955A (en) 1960-10-29 1961-10-12 Construction of turbomachinery blade elements

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB37254/60A GB938189A (en) 1960-10-29 1960-10-29 Improvements in the construction of turbine and compressor blade elements

Publications (1)

Publication Number Publication Date
GB938189A true GB938189A (en) 1963-10-02

Family

ID=10394995

Family Applications (1)

Application Number Title Priority Date Filing Date
GB37254/60A Expired GB938189A (en) 1960-10-29 1960-10-29 Improvements in the construction of turbine and compressor blade elements

Country Status (2)

Country Link
US (1) US3182955A (en)
GB (1) GB938189A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2223276A (en) * 1988-09-30 1990-04-04 Rolls Royce Plc Cooling turbine blade shrouds
GB2260789A (en) * 1991-09-27 1993-04-28 Gen Electric Mounting arrangements for turbine nozzles.

Families Citing this family (28)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3365173A (en) * 1966-02-28 1968-01-23 Gen Electric Stator structure
US3527544A (en) * 1968-12-12 1970-09-08 Gen Motors Corp Cooled blade shroud
US3628226A (en) * 1970-03-16 1971-12-21 Aerojet General Co Method of making hollow compressor blades
GB1605309A (en) * 1975-03-14 1989-02-01 Rolls Royce Stator blade for a gas turbine engine
US4015910A (en) * 1976-03-09 1977-04-05 The United States Of America As Represented By The Secretary Of The Air Force Bolted paired vanes for turbine
US4688988A (en) * 1984-12-17 1987-08-25 United Technologies Corporation Coolable stator assembly for a gas turbine engine
CH667611A5 (en) * 1985-02-28 1988-10-31 Bbc Brown Boveri & Cie METHOD FOR PRODUCING A CONTROL WHEEL FOR THE HIGH PRESSURE ROTOR OF A STEAM TURBINE.
GB2207629B (en) * 1987-07-22 1991-01-02 Rolls Royce Plc Method of manufacture of an axial flow compressor assembly
US4902198A (en) * 1988-08-31 1990-02-20 Westinghouse Electric Corp. Apparatus for film cooling of turbine van shrouds
EP0921273B1 (en) * 1997-06-11 2003-12-03 Mitsubishi Heavy Industries, Ltd. Rotor for gas turbines
US6210111B1 (en) * 1998-12-21 2001-04-03 United Technologies Corporation Turbine blade with platform cooling
EP1022437A1 (en) * 1999-01-19 2000-07-26 Siemens Aktiengesellschaft Construction element for use in a thermal machine
US6553665B2 (en) * 2000-03-08 2003-04-29 General Electric Company Stator vane assembly for a turbine and method for forming the assembly
US7597542B2 (en) * 2005-08-30 2009-10-06 General Electric Company Methods and apparatus for controlling contact within stator assemblies
EP1892383A1 (en) * 2006-08-24 2008-02-27 Siemens Aktiengesellschaft Gas turbine blade with cooled platform
US8220150B2 (en) 2007-05-22 2012-07-17 United Technologies Corporation Split vane cluster repair method
US7798773B2 (en) * 2007-08-06 2010-09-21 United Technologies Corporation Airfoil replacement repair
US20090274562A1 (en) * 2008-05-02 2009-11-05 United Technologies Corporation Coated turbine-stage nozzle segments
US8245399B2 (en) * 2009-01-20 2012-08-21 United Technologies Corporation Replacement of part of engine case with dissimilar material
US8092159B2 (en) * 2009-03-31 2012-01-10 General Electric Company Feeding film cooling holes from seal slots
US9133855B2 (en) * 2010-11-15 2015-09-15 Mtu Aero Engines Gmbh Rotor for a turbo machine
US8763403B2 (en) 2010-11-19 2014-07-01 United Technologies Corporation Method for use with annular gas turbine engine component
US8888459B2 (en) * 2011-08-23 2014-11-18 General Electric Company Coupled blade platforms and methods of sealing
US9631517B2 (en) 2012-12-29 2017-04-25 United Technologies Corporation Multi-piece fairing for monolithic turbine exhaust case
US9920642B2 (en) * 2013-03-15 2018-03-20 Ansaldo Energia Ip Uk Limited Compressor airfoil
WO2015017040A2 (en) * 2013-07-30 2015-02-05 United Technologies Corporation Gas turbine engine vane ring arrangement
US20190085706A1 (en) * 2017-09-18 2019-03-21 General Electric Company Turbine engine airfoil assembly
EP4202186A1 (en) * 2021-12-27 2023-06-28 Rolls-Royce plc Turbine blade

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1470508A (en) * 1921-12-23 1923-10-09 Gen Electric Method of manufacturing turbine elements
US2398140A (en) * 1943-12-08 1946-04-09 Armstrong Siddeley Motors Ltd Bladed rotor
US2500745A (en) * 1944-09-21 1950-03-14 Gen Electric Bucket structure for high-temperature turbomachines
US2510734A (en) * 1946-04-06 1950-06-06 United Aircraft Corp Turbine or compressor rotor
US2603453A (en) * 1946-09-11 1952-07-15 Curtiss Wright Corp Cooling means for turbines
US2639119A (en) * 1947-11-14 1953-05-19 Lockheed Aircraft Corp Rotor blade attachment means and method
US2646209A (en) * 1948-05-21 1953-07-21 Galliot Jules Andre Norbert Turbine driven multistage compressor
GB727608A (en) * 1951-10-31 1955-04-06 Gen Motors Corp Improvements in blade assemblies for gas turbines and the like
GB740909A (en) * 1953-02-02 1955-11-23 Bristol Aeroplane Co Ltd Improvements in or relating to aerofoil blade assemblies
BE533039A (en) * 1953-11-06
US2819870A (en) * 1955-04-18 1958-01-14 Oleh A Wayne Sheet metal blade base
GB846277A (en) * 1956-11-20 1960-08-31 Rolls Royce Turbine and compressor blades
US2931622A (en) * 1956-12-24 1960-04-05 Orenda Engines Ltd Rotor construction for gas turbine engines

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2223276A (en) * 1988-09-30 1990-04-04 Rolls Royce Plc Cooling turbine blade shrouds
GB2223276B (en) * 1988-09-30 1992-09-02 Rolls Royce Plc Turbine aerofoil blade
GB2260789A (en) * 1991-09-27 1993-04-28 Gen Electric Mounting arrangements for turbine nozzles.
GB2260789B (en) * 1991-09-27 1994-11-16 Gen Electric Mounting arrangements for turbine nozzles

Also Published As

Publication number Publication date
US3182955A (en) 1965-05-11

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