GB736835A - Improvements in or relating to blading for axial flow turbo-engines - Google Patents

Improvements in or relating to blading for axial flow turbo-engines

Info

Publication number
GB736835A
GB736835A GB22920/53A GB2292053A GB736835A GB 736835 A GB736835 A GB 736835A GB 22920/53 A GB22920/53 A GB 22920/53A GB 2292053 A GB2292053 A GB 2292053A GB 736835 A GB736835 A GB 736835A
Authority
GB
United Kingdom
Prior art keywords
blade
slot
energy side
root
turbine
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
GB22920/53A
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.)
MAN AG
Original Assignee
MAN Maschinenfabrik Augsburg Nuernberg 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 MAN Maschinenfabrik Augsburg Nuernberg AG filed Critical MAN Maschinenfabrik Augsburg Nuernberg AG
Publication of GB736835A publication Critical patent/GB736835A/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
    • F01D5/14—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)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

736,835. Turbine blades. MASCHINENFABRIK AUGSBURG-NURNBERG AKT.- GES. Aug. 19, 1953 [Sept. 11, 1952], No. 22920/53. Class 110 (3). [Also in Group XXXIII] An unshrouded axial flow turbine blade has at least one aperture in that zone of the blade near the rotor hub wall or the turbine casing, the flow near such zones being subject to an edge effect, through which aperture a portion of the operating medium is intended to be guided from the high energy side of the blade to the low energy side. Fig. 2 shows a blade 5 with a slot 6 inclined from the radial direction towards the direction of rotation, and having parallel walls 7, 8. The slot is preferably onefifth of the blade height, and may be orientated in the radial direction. A cross-section is shown in Fig. 4, where the outlet of the slot is preferably situated at the end c of that portion a-b-c-d of the flow channel bounded by adjacent blades. The slot 13 may have parallel sides or form a convergent nozzle as shown. The apertures may take the form of diagonal bores 22 (Fig. 5) starting from a position remote from the root or tip on the high energy side and finishing at a position close to the root or tip on the low energy side.
GB22920/53A 1952-09-11 1953-08-19 Improvements in or relating to blading for axial flow turbo-engines Expired GB736835A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE736835X 1952-09-11

Publications (1)

Publication Number Publication Date
GB736835A true GB736835A (en) 1955-09-14

Family

ID=6642416

Family Applications (1)

Application Number Title Priority Date Filing Date
GB22920/53A Expired GB736835A (en) 1952-09-11 1953-08-19 Improvements in or relating to blading for axial flow turbo-engines

Country Status (1)

Country Link
GB (1) GB736835A (en)

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4102600A (en) * 1975-04-09 1978-07-25 Maschinenfabrik Augsburg-Nurnberg Aktiengesellschaft Moving blade ring of high circumferential speed for thermal axially passed through turbines
US4274806A (en) * 1979-06-18 1981-06-23 General Electric Company Staircase blade tip
EP0169730A1 (en) * 1984-07-27 1986-01-29 The Secretary of State for Defence in Her Britannic Majesty's Government of the United Kingdom of Great Britain and Improvements in or relating to fluid excitation alleviation
US4930981A (en) * 1989-08-18 1990-06-05 Walker Manufacturing Company Low noise impeller
US6435815B2 (en) 2000-01-22 2002-08-20 Rolls-Royce Plc Aerofoil for an axial flow turbo machine
GB2418471A (en) * 2004-09-28 2006-03-29 Gen Electric Bleeding a boundary layer from an aerofoil
EP2006488A2 (en) * 2006-04-07 2008-12-24 IHI Corporation Axial flow fluid device and blade
EP2267275A2 (en) 2009-06-24 2010-12-29 Rolls-Royce plc A shroudless blade
GB2481822A (en) * 2010-07-07 2012-01-11 Rolls Royce Plc Rotor blade with air flow passages
EP2725233A1 (en) * 2012-10-26 2014-04-30 Honeywell International Inc. Rotor blade for a compressor
WO2015065659A1 (en) 2013-10-31 2015-05-07 United Technologies Corporation Gas turbine engine airfoil with auxiliary flow channel
GB2588955A (en) * 2019-11-15 2021-05-19 Rolls Royce Plc A turbomachine blade

Cited By (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4102600A (en) * 1975-04-09 1978-07-25 Maschinenfabrik Augsburg-Nurnberg Aktiengesellschaft Moving blade ring of high circumferential speed for thermal axially passed through turbines
US4274806A (en) * 1979-06-18 1981-06-23 General Electric Company Staircase blade tip
EP0169730A1 (en) * 1984-07-27 1986-01-29 The Secretary of State for Defence in Her Britannic Majesty's Government of the United Kingdom of Great Britain and Improvements in or relating to fluid excitation alleviation
US4930981A (en) * 1989-08-18 1990-06-05 Walker Manufacturing Company Low noise impeller
US6435815B2 (en) 2000-01-22 2002-08-20 Rolls-Royce Plc Aerofoil for an axial flow turbo machine
GB2418471A (en) * 2004-09-28 2006-03-29 Gen Electric Bleeding a boundary layer from an aerofoil
US7320575B2 (en) 2004-09-28 2008-01-22 General Electric Company Methods and apparatus for aerodynamically self-enhancing rotor blades
GB2418471B (en) * 2004-09-28 2010-01-06 Gen Electric Methods and apparatus for aerodynamically self-enhancing rotor blades
EP2006488A2 (en) * 2006-04-07 2008-12-24 IHI Corporation Axial flow fluid device and blade
EP2006488A4 (en) * 2006-04-07 2013-04-17 Ihi Corp Axial flow fluid device and blade
EP2267275A3 (en) * 2009-06-24 2017-10-18 Rolls-Royce plc A shroudless blade
EP2267275A2 (en) 2009-06-24 2010-12-29 Rolls-Royce plc A shroudless blade
GB2481822A (en) * 2010-07-07 2012-01-11 Rolls Royce Plc Rotor blade with air flow passages
US8764380B2 (en) 2010-07-07 2014-07-01 Rolls-Royce Plc Rotor blade
GB2481822B (en) * 2010-07-07 2013-09-18 Rolls Royce Plc Rotor blade
EP2725233A1 (en) * 2012-10-26 2014-04-30 Honeywell International Inc. Rotor blade for a compressor
WO2015065659A1 (en) 2013-10-31 2015-05-07 United Technologies Corporation Gas turbine engine airfoil with auxiliary flow channel
US20160245091A1 (en) * 2013-10-31 2016-08-25 United Technologies Corporation Gas turbine engine airfoil with auxiliary flow channel
EP3063374A4 (en) * 2013-10-31 2017-08-09 United Technologies Corporation Gas turbine engine airfoil with auxiliary flow channel
US10280757B2 (en) 2013-10-31 2019-05-07 United Technologies Corporation Gas turbine engine airfoil with auxiliary flow channel
GB2588955A (en) * 2019-11-15 2021-05-19 Rolls Royce Plc A turbomachine blade

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