GB793143A - Improvements relating to axial-flow compressors - Google Patents

Improvements relating to axial-flow compressors

Info

Publication number
GB793143A
GB793143A GB1540456A GB1540456A GB793143A GB 793143 A GB793143 A GB 793143A GB 1540456 A GB1540456 A GB 1540456A GB 1540456 A GB1540456 A GB 1540456A GB 793143 A GB793143 A GB 793143A
Authority
GB
United Kingdom
Prior art keywords
blade
axial
flange
flow
suction side
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
GB1540456A
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.)
Daimler Benz AG
Original Assignee
Daimler Benz AG
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 Daimler Benz AG filed Critical Daimler Benz AG
Priority to GB1540456A priority Critical patent/GB793143A/en
Publication of GB793143A publication Critical patent/GB793143A/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
    • F01D5/145—Means for influencing boundary layers or secondary circulations

Landscapes

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

Abstract

793,143. Axial-flow compressors. DAIMLERBENZ AKT.-GES. May 17, 1956 [May 18, 1955], No. 15404/56. Class 110 (1). In an axial-flow compressor with swept-back blading, at least one collar extending at least approximately at a constant distance from the principal axis of the compressor and acting as a boundary-layer fence is disposed on the surface of a blade. The leading edge 1, Fig. 1, of an axial flow compressor blade is swept back, as shown, to reduce the relative velocity. Radial flow of the boundary layer is reduced by flanges 3, 4. Flange 3 extends from the leading edge 1 for about two-thirds of the blade length on the suction side 5 and about half the blade length on the pressure side 6, as shown in Fig. 4. Flange 4 extends for about one-half to twothirds of the blade length on the suction side only. In a modification, flange 3 extends completely around the blade profile, its width being greater on the suction side of the blade than;on the pressure side.
GB1540456A 1956-05-17 1956-05-17 Improvements relating to axial-flow compressors Expired GB793143A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB1540456A GB793143A (en) 1956-05-17 1956-05-17 Improvements relating to axial-flow compressors

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1540456A GB793143A (en) 1956-05-17 1956-05-17 Improvements relating to axial-flow compressors

Publications (1)

Publication Number Publication Date
GB793143A true GB793143A (en) 1958-04-09

Family

ID=6708878

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1540456A Expired GB793143A (en) 1956-05-17 1956-05-17 Improvements relating to axial-flow compressors

Country Status (1)

Country Link
GB (1) GB793143A (en)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3014640A (en) * 1958-06-09 1961-12-26 Gen Motors Corp Axial flow compressor
US3193185A (en) * 1962-10-29 1965-07-06 Gen Electric Compressor blading
EP0978633A1 (en) * 1998-08-07 2000-02-09 Asea Brown Boveri AG Turbomachine blade
FR2867506A1 (en) * 2004-03-11 2005-09-16 Snecma Moteurs Guide vane for use on stator of jet engine, has rib directed in direction of gas flow traversing vane for dampening vibrations of vane, and placed at back side of vane closer to trailing edge than leading edge of vane
US9593584B2 (en) 2012-10-26 2017-03-14 Rolls-Royce Plc Turbine rotor blade of a gas turbine
US11047246B2 (en) * 2018-04-27 2021-06-29 MTU Aero Engines AG Blade or vane, blade or vane segment and assembly for a turbomachine, and turbomachine

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3014640A (en) * 1958-06-09 1961-12-26 Gen Motors Corp Axial flow compressor
US3193185A (en) * 1962-10-29 1965-07-06 Gen Electric Compressor blading
EP0978633A1 (en) * 1998-08-07 2000-02-09 Asea Brown Boveri AG Turbomachine blade
FR2867506A1 (en) * 2004-03-11 2005-09-16 Snecma Moteurs Guide vane for use on stator of jet engine, has rib directed in direction of gas flow traversing vane for dampening vibrations of vane, and placed at back side of vane closer to trailing edge than leading edge of vane
US9593584B2 (en) 2012-10-26 2017-03-14 Rolls-Royce Plc Turbine rotor blade of a gas turbine
US10641107B2 (en) 2012-10-26 2020-05-05 Rolls-Royce Plc Turbine blade with tip overhang along suction side
US11047246B2 (en) * 2018-04-27 2021-06-29 MTU Aero Engines AG Blade or vane, blade or vane segment and assembly for a turbomachine, and turbomachine

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