GB719061A - Blade arrangement for improving the performance of a gas turbine plant - Google Patents

Blade arrangement for improving the performance of a gas turbine plant

Info

Publication number
GB719061A
GB719061A GB6500/51A GB650051A GB719061A GB 719061 A GB719061 A GB 719061A GB 6500/51 A GB6500/51 A GB 6500/51A GB 650051 A GB650051 A GB 650051A GB 719061 A GB719061 A GB 719061A
Authority
GB
United Kingdom
Prior art keywords
vane
axial
gas turbine
turbine plant
blades
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
GB6500/51A
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.)
Raytheon Technologies Corp
Original Assignee
United Aircraft Corp
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 United Aircraft Corp filed Critical United Aircraft Corp
Publication of GB719061A publication Critical patent/GB719061A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • 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
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/324—Blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • F04D29/544—Blade shapes
    • 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

719,061. Gas turbine plant; axial-flow compressors. UNITED AIRCRAFT CORPORATION. March 19, 1951 [June 21, 1950; July 27, 1950], No. 6500/51. Classes 110(1) and 110(3) In an axial-flow gas turbine plant having an air compressor with co-operating rotor and stator blades, some or all of the blades have modified end portions which increase the axial component of the gas flow near the wall or boundary of the gas flow path with respect to the axial component of the gas flow more remotely spaced therefrom. The vane shown in Fig. 2 is an inlet guide vane of the axial-flow compressor of a gas turbine plant. The mid-portion 32 of the vane is cambered so that air is directed on to the first row of rotor blades at the desired angle. The end portions 28, 30 of the vane are of substantially symmetrical cross-section as shown at 34, 36 so that air flows over these portions in an approximately axial direction. The axial component of the air flowing near the walls 16, 20 is therefore greater than that of the air flowing over the cambered part of the vane. In the embodiment shown in Fig. 3 the inlet guide vane 38 is supported solely by struts 40, 42 while in Fig. 4, the guide vane 44 is supported at one end only by a strut 46. End portions of the rotor blades 26 and stator blades 128 may be modified as shown in Fig. 7, the aerfoil-section rotor blade 26 having its tip portion 134 overcambered, while the radiallyinward end of the stator blade 128 is overcambered as indicated at 138.
GB6500/51A 1950-06-21 1951-03-19 Blade arrangement for improving the performance of a gas turbine plant Expired GB719061A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US719061XA 1950-06-21 1950-06-21

Publications (1)

Publication Number Publication Date
GB719061A true GB719061A (en) 1954-11-24

Family

ID=22104359

Family Applications (1)

Application Number Title Priority Date Filing Date
GB6500/51A Expired GB719061A (en) 1950-06-21 1951-03-19 Blade arrangement for improving the performance of a gas turbine plant

Country Status (1)

Country Link
GB (1) GB719061A (en)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0251978A2 (en) * 1986-05-28 1988-01-07 United Technologies Corporation Stator vane
FR2623243A1 (en) * 1987-11-12 1989-05-19 Mtu Muenchen Gmbh GUIDE CROWN FOR A GAS TURBINE WITH AN INTERNAL RING, AN EXTERNAL RING ONE OF WHICH IS SEPARATELY DISPOSABLE AND LIKELY TO BE MOVED SEPARATELY
US5246339A (en) * 1988-06-08 1993-09-21 Abb Flakt Ab Guide vane for an axial fan
EP0661413A1 (en) * 1993-12-23 1995-07-05 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Axial blade cascade with blades of arrowed leading edge
CH687347A5 (en) * 1993-04-08 1996-11-15 Abb Management Ag Heat generator.
WO1998054471A1 (en) * 1997-05-28 1998-12-03 Ksb Aktiengesellschaft Centrifugal pump with inflow guide device
EP2103782A1 (en) * 2007-01-12 2009-09-23 Mitsubishi Heavy Industries, Ltd. Blade structure for gas turbine
EP1760321A3 (en) * 2005-09-05 2011-07-27 Rolls-Royce Deutschland Ltd & Co KG Blade for turbomachine

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0251978A2 (en) * 1986-05-28 1988-01-07 United Technologies Corporation Stator vane
EP0251978A3 (en) * 1986-05-28 1989-05-24 United Technologies Corporation Stator vane
FR2623243A1 (en) * 1987-11-12 1989-05-19 Mtu Muenchen Gmbh GUIDE CROWN FOR A GAS TURBINE WITH AN INTERNAL RING, AN EXTERNAL RING ONE OF WHICH IS SEPARATELY DISPOSABLE AND LIKELY TO BE MOVED SEPARATELY
US4909708A (en) * 1987-11-12 1990-03-20 Mtu Motoren- Und Turbinen- Union Munchen Gmbh Vane assembly for a gas turbine
US5246339A (en) * 1988-06-08 1993-09-21 Abb Flakt Ab Guide vane for an axial fan
CH687347A5 (en) * 1993-04-08 1996-11-15 Abb Management Ag Heat generator.
US5647200A (en) * 1993-04-08 1997-07-15 Asea Brown Boveri Ag Heat generator
EP0661413A1 (en) * 1993-12-23 1995-07-05 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Axial blade cascade with blades of arrowed leading edge
WO1998054471A1 (en) * 1997-05-28 1998-12-03 Ksb Aktiengesellschaft Centrifugal pump with inflow guide device
EP1760321A3 (en) * 2005-09-05 2011-07-27 Rolls-Royce Deutschland Ltd & Co KG Blade for turbomachine
EP2103782A1 (en) * 2007-01-12 2009-09-23 Mitsubishi Heavy Industries, Ltd. Blade structure for gas turbine
EP2103782A4 (en) * 2007-01-12 2013-10-30 Mitsubishi Heavy Ind Ltd Blade structure for gas turbine

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