FR2181407A5 - - Google Patents

Info

Publication number
FR2181407A5
FR2181407A5 FR7314544A FR7314544A FR2181407A5 FR 2181407 A5 FR2181407 A5 FR 2181407A5 FR 7314544 A FR7314544 A FR 7314544A FR 7314544 A FR7314544 A FR 7314544A FR 2181407 A5 FR2181407 A5 FR 2181407A5
Authority
FR
France
Prior art keywords
vane
blade
over
april
cap
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
FR7314544A
Other languages
French (fr)
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Application granted granted Critical
Publication of FR2181407A5 publication Critical patent/FR2181407A5/fr
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
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • 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
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • 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
    • 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

Abstract

1423833 Turbine and like blades ROLLSROYCE (1971) Ltd 19 April 1973 [20 April 1972] 18488/72 Heading F1T Leakage flow over the tips of gas turbine engine rotor blades 19 is utilized to help drive the rotor by providing an inclined vane 27 on the tip of each blade. As shown, the vane 27 varies in radial height over its length, and is formed on a blade shroud 25 with sealing lips 26 co-operating with a sealing lining 30. As shown in broken line, the vane is of constant height over its length. It may be curved, inclined to a radial plane or turned over at its radially outer end, Fig. 4c, (not shown). It may be formed adjacent exit holes (34), Fig. 4b, (not shown), in the blade tip for cooling air flowing in channels longitudinally of the blade. Also, the exit holes may be covered by a cap (52), Fig. 5a, (not shown), adapted to deflect the cooling air on to a vane (58), or the vane may be formed on top of such a cap, as described in 48598/72.
FR7314544A 1972-04-20 1973-04-20 Expired FR2181407A5 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1848872A GB1423833A (en) 1972-04-20 1972-04-20 Rotor blades for fluid flow machines

Publications (1)

Publication Number Publication Date
FR2181407A5 true FR2181407A5 (en) 1973-11-30

Family

ID=10113289

Family Applications (1)

Application Number Title Priority Date Filing Date
FR7314544A Expired FR2181407A5 (en) 1972-04-20 1973-04-20

Country Status (4)

Country Link
US (1) US3876330A (en)
DE (1) DE2319743A1 (en)
FR (1) FR2181407A5 (en)
GB (1) GB1423833A (en)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2405357A1 (en) * 1977-10-08 1979-05-04 Rolls Royce MOBILE REFRIGERATED VANE FOR GAS TURBINE ENGINE
FR2481740A1 (en) * 1980-05-01 1981-11-06 Gen Electric ROTOR BOLT FOR ROTOR BLADE
FR2977909A1 (en) * 2011-07-12 2013-01-18 Snecma Blade for rotor of low-pressure turbine of e.g. turbojet of aircraft, has knife edge comprising internal part and external part that is tilted relative to axis, where knife edge extends from outer end to outside in direction of leading edge
FR3053385A1 (en) * 2016-06-29 2018-01-05 Safran Helicopter Engines TURBOMACHINE WHEEL
FR3053386A1 (en) * 2016-06-29 2018-01-05 Safran Helicopter Engines TURBINE WHEEL
WO2019122540A1 (en) * 2017-12-19 2019-06-27 Safran Helicopter Engines Turbomachine wheel with convex or concave lips

Families Citing this family (53)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4370094A (en) * 1974-03-21 1983-01-25 Maschinenfabrik Augsburg-Nurnberg Aktiengesellschaft Method of and device for avoiding rotor instability to enhance dynamic power limit of turbines and compressors
GB1514613A (en) * 1976-04-08 1978-06-14 Rolls Royce Blade or vane for a gas turbine engine
JPS5338806A (en) * 1976-09-22 1978-04-10 Hitachi Ltd Seal device for nose part of movable vane
US4214355A (en) * 1977-12-21 1980-07-29 General Electric Company Method for repairing a turbomachinery blade tip
US4332523A (en) * 1979-05-25 1982-06-01 Teledyne Industries, Inc. Turbine shroud assembly
US4274806A (en) * 1979-06-18 1981-06-23 General Electric Company Staircase blade tip
US4606701A (en) * 1981-09-02 1986-08-19 Westinghouse Electric Corp. Tip structure for a cooled turbine rotor blade
US4534701A (en) * 1982-06-29 1985-08-13 Gerhard Wisser Rotor or guide wheel of a turbine engine with shroud ring
GB2127104A (en) * 1982-08-11 1984-04-04 Rolls Royce Sealing means for a turbine rotor blade in a gas turbine engine
US4487550A (en) * 1983-01-27 1984-12-11 The United States Of America As Represented By The Secretary Of The Air Force Cooled turbine blade tip closure
DE3308140C2 (en) * 1983-03-08 1985-12-19 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Multi-stage gas turbine
GB2146707B (en) * 1983-09-14 1987-08-05 Rolls Royce Turbine
DE3401742C2 (en) * 1984-01-19 1986-08-14 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Rotor for an axial compressor
DE3505491A1 (en) * 1985-02-16 1986-08-21 MTU Motoren- und Turbinen-Union München GmbH, 8000 München GASKET FOR A FLUID MACHINE
US4909706A (en) * 1987-01-28 1990-03-20 Union Carbide Corporation Controlled clearance labyrinth seal
US4761116A (en) * 1987-05-11 1988-08-02 General Electric Company Turbine blade with tip vent
GB2223276B (en) * 1988-09-30 1992-09-02 Rolls Royce Plc Turbine aerofoil blade
EP0528138B1 (en) * 1991-08-08 1995-05-17 Asea Brown Boveri Ag Blade shroud for axial turbine
DE59201833D1 (en) * 1991-10-08 1995-05-11 Asea Brown Boveri Shroud for turbine with axial flow.
US5632598A (en) * 1995-01-17 1997-05-27 Dresser-Rand Shrouded axial flow turbo machine utilizing multiple labrinth seals
JP2955252B2 (en) * 1997-06-26 1999-10-04 三菱重工業株式会社 Gas turbine blade tip shroud
EP0903468B1 (en) * 1997-09-19 2003-08-20 ALSTOM (Switzerland) Ltd Gap sealing device
GB2340189A (en) * 1998-08-04 2000-02-16 Siemens Plc A turbomachine shroud seal having baffles
EP1013884B1 (en) 1998-12-24 2005-07-27 ALSTOM Technology Ltd Turbine blade with actively cooled head platform
DE19860245A1 (en) * 1998-12-24 2000-06-29 Abb Alstom Power Ch Ag Air cooled blade for gas turbine has cooling holes in shroud element running from inside outwards and parallel to direction of blade's movement, with each cooling hole opening out into surface recess before outer edge of shroud element
EP1041247B1 (en) * 1999-04-01 2012-08-01 General Electric Company Gas turbine airfoil comprising an open cooling circuit
US6761534B1 (en) * 1999-04-05 2004-07-13 General Electric Company Cooling circuit for a gas turbine bucket and tip shroud
US6296459B1 (en) 2000-02-15 2001-10-02 Intex Recreation Corp. Electric air pump having multiple impellers and method
GB0228443D0 (en) * 2002-12-06 2003-01-08 Rolls Royce Plc Blade cooling
GB0319002D0 (en) * 2003-05-13 2003-09-17 Alstom Switzerland Ltd Improvements in or relating to steam turbines
US7836591B2 (en) * 2005-03-17 2010-11-23 Siemens Energy, Inc. Method for forming turbine seal by cold spray process
US8317465B2 (en) * 2009-07-02 2012-11-27 General Electric Company Systems and apparatus relating to turbine engines and seals for turbine engines
US8608424B2 (en) * 2009-10-09 2013-12-17 General Electric Company Contoured honeycomb seal for a turbomachine
US8556575B2 (en) * 2010-03-26 2013-10-15 United Technologies Corporation Blade outer seal for a gas turbine engine
EP2412927A1 (en) * 2010-07-29 2012-02-01 Alstom Technology Ltd Turbine blade
GB201017797D0 (en) * 2010-10-21 2010-12-01 Rolls Royce Plc An aerofoil structure
US9097136B2 (en) * 2012-01-03 2015-08-04 General Electric Company Contoured honeycomb seal for turbine shroud
US9080459B2 (en) * 2012-01-03 2015-07-14 General Electric Company Forward step honeycomb seal for turbine shroud
US10287914B2 (en) 2012-01-31 2019-05-14 United Technologies Corporation Gas turbine engine with high speed low pressure turbine section and bearing support features
US20130230379A1 (en) * 2012-03-01 2013-09-05 General Electric Company Rotating turbomachine component having a tip leakage flow guide
US10125693B2 (en) 2012-04-02 2018-11-13 United Technologies Corporation Geared turbofan engine with power density range
US9291061B2 (en) * 2012-04-13 2016-03-22 General Electric Company Turbomachine blade tip shroud with parallel casing configuration
JP6012519B2 (en) * 2013-03-21 2016-10-25 三菱重工業株式会社 Turbine and rotating machine equipped with the same
US20160003163A1 (en) * 2014-07-03 2016-01-07 United Technologies Corporation Gas turbine engine with short transition duct
EP3034790B1 (en) * 2014-12-16 2020-06-24 Ansaldo Energia Switzerland AG Rotating blade for a gas turbine
EP3085890B1 (en) * 2015-04-22 2017-12-27 Ansaldo Energia Switzerland AG Blade with tip shroud
GB201519869D0 (en) * 2015-11-11 2015-12-23 Rolls Royce Plc Shrouded turbine blade
DE102016222720A1 (en) * 2016-11-18 2018-05-24 MTU Aero Engines AG Sealing system for an axial flow machine and axial flow machine
US10502069B2 (en) 2017-06-07 2019-12-10 General Electric Company Turbomachine rotor blade
US11060407B2 (en) 2017-06-22 2021-07-13 General Electric Company Turbomachine rotor blade
US10590777B2 (en) 2017-06-30 2020-03-17 General Electric Company Turbomachine rotor blade
US10577945B2 (en) 2017-06-30 2020-03-03 General Electric Company Turbomachine rotor blade
US10301943B2 (en) 2017-06-30 2019-05-28 General Electric Company Turbomachine rotor blade

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1010750A (en) * 1909-04-28 1911-12-05 Colonial Trust Co Turbine-balde shroud.
GB855058A (en) * 1957-02-22 1960-11-30 Rolls Royce Improvements in or relating to bladed rotor or stator constructions for axial-flow fluid machines for example for compressors or turbines of gas-turbine engines
US3533712A (en) * 1966-02-26 1970-10-13 Gen Electric Cooled vane structure for high temperature turbines
US3575523A (en) * 1968-12-05 1971-04-20 Us Navy Labyrinth seal for axial flow fluid machines
US3527544A (en) * 1968-12-12 1970-09-08 Gen Motors Corp Cooled blade shroud
US3606572A (en) * 1969-08-25 1971-09-20 Gen Motors Corp Airfoil with porous leading edge
US3635585A (en) * 1969-12-23 1972-01-18 Westinghouse Electric Corp Gas-cooled turbine blade
US3736071A (en) * 1970-11-27 1973-05-29 Gen Electric Bucket tip/collection slot combination for open-circuit liquid-cooled gas turbines

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2405357A1 (en) * 1977-10-08 1979-05-04 Rolls Royce MOBILE REFRIGERATED VANE FOR GAS TURBINE ENGINE
FR2481740A1 (en) * 1980-05-01 1981-11-06 Gen Electric ROTOR BOLT FOR ROTOR BLADE
FR2977909A1 (en) * 2011-07-12 2013-01-18 Snecma Blade for rotor of low-pressure turbine of e.g. turbojet of aircraft, has knife edge comprising internal part and external part that is tilted relative to axis, where knife edge extends from outer end to outside in direction of leading edge
FR3053385A1 (en) * 2016-06-29 2018-01-05 Safran Helicopter Engines TURBOMACHINE WHEEL
FR3053386A1 (en) * 2016-06-29 2018-01-05 Safran Helicopter Engines TURBINE WHEEL
WO2019122540A1 (en) * 2017-12-19 2019-06-27 Safran Helicopter Engines Turbomachine wheel with convex or concave lips

Also Published As

Publication number Publication date
US3876330A (en) 1975-04-08
DE2319743A1 (en) 1973-10-31
GB1423833A (en) 1976-02-04

Similar Documents

Publication Publication Date Title
FR2181407A5 (en)
GB1357713A (en) Cooled rotor blades for gas turbines
GB1457914A (en) Turbomachinery rotor blades and tip caps therefor
GB1331206A (en) Vane structure for gas turbine
FR2117848A1 (en)
GB1426049A (en) Rotor blade for a gas turbine engine
GB1177410A (en) Improvements in Gas Turbine Engine Turbine Rotor Shrouds
GB1327317A (en) Gas turbines
GB1465282A (en) Leakage control structure
GB1088360A (en) Improvements in gas turbine ducted fan engine sealing means
GB1491556A (en) Rotor blades for turbomachines
GB1497619A (en) Turbine blade tip seal
GB1376966A (en) Porous abradable seal structures
GB1306575A (en) Segmented seal assembly for axial flow turbines
GB1514613A (en) Blade or vane for a gas turbine engine
GB1437617A (en) Gas turbine
GB1462470A (en) Axial flow reaction turbine
GB1195012A (en) Rotor for Bladed Fluid Flow Machines.
GB1304678A (en)
GB1219994A (en) Turbine for a compressible medium
KR840006397A (en) One-stage rotor blades for combustion turbine
FR2323007A1 (en) Turbine blade cooling by fluid leakage through void by blade root - has void wall, with inclined coutlet bore, radial to blade platform
GB1311776A (en) Cooled shrouded turbine blade
GB1404757A (en) Gas turbine engine blades
FR2324873A1 (en) Axial flow turbomachinery rotor - has turbine blade fixing ring which also acts as stage seal

Legal Events

Date Code Title Description
CD Change of name or company name