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GB1331209A - Bladed rotors for fluid flow machines - Google Patents

Bladed rotors for fluid flow machines

Info

Publication number
GB1331209A
GB1331209A GB1331209DA GB1331209A GB 1331209 A GB1331209 A GB 1331209A GB 1331209D A GB1331209D A GB 1331209DA GB 1331209 A GB1331209 A GB 1331209A
Authority
GB
United Kingdom
Prior art keywords
spacer
walls
secured
fluid flow
flanges
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
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.)
UK Secretary of State for Defence
Original Assignee
UK Secretary of State for Defence
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 UK Secretary of State for Defence filed Critical UK Secretary of State for Defence
Publication of GB1331209A publication Critical patent/GB1331209A/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
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/005—Sealing means between non relatively rotating elements
    • F01D11/006—Sealing the gap between rotor blades or blades and rotor
    • F01D11/008—Sealing the gap between rotor blades or blades and rotor by spacer elements between the blades, e.g. independent interblade platforms

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

1331209 Turbomachine rotors DEFENCE SECRETARY OF STATE FOR 27 July 1972 35114/72 Addition to 1232506 Heading FIT The rotor blade spacer described in Specification 1232506 is modified by the provision of axially extending flanges 40, 41 on radial bracing walls 24, 25 respectively, the flanges co-operating with elastomer sealing strips 45 secured to the flanks of circumferentially adjacent blades 12. The walls 24, 25 extend the full axial length of the spacer. An additional glass reinforced plastics reinforcing wall 44 is provided. Each spacer may be secured to rotor 33, e.g. the front fan of a gas turbine ducted fan engine, by a bolt 32 located in a recess 30 of a mushroom shaped member 31 bonded within holes 38, 38' in walls 15, 16 respectively. The upstream end 22 of each spacer fits into a nose cone 35.
GB1331209D 1969-10-28 1972-07-27 Bladed rotors for fluid flow machines Expired GB1331209A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB5274769 1969-10-28
GB3511472 1972-07-27

Publications (1)

Publication Number Publication Date
GB1331209A true GB1331209A (en) 1973-09-26

Family

ID=26262580

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1331209D Expired GB1331209A (en) 1969-10-28 1972-07-27 Bladed rotors for fluid flow machines

Country Status (1)

Country Link
GB (1) GB1331209A (en)

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2654773A1 (en) * 1989-11-22 1991-05-24 Snecma AXIAL FLOW TURBOMACHINE ROTOR.
GB2257755A (en) * 1991-07-17 1993-01-20 Snecma Interblade platform.
WO1993022539A1 (en) * 1992-05-07 1993-11-11 Rolls-Royce Plc Rotors for gas turbine engines
FR2706528A1 (en) * 1993-06-10 1994-12-23 Snecma Separate inter-blade platform of turbine engine rotor blade disc.
FR2716502A1 (en) * 1994-02-23 1995-08-25 Snecma Sealing between vanes and intermediate platforms.
EP0677645A1 (en) * 1994-03-19 1995-10-18 ROLLS-ROYCE plc A gas turbine engine fan blade assembly
WO1997044570A1 (en) * 1996-05-20 1997-11-27 Pratt & Whitney Canada Inc. Gas turbine engine shroud seals
US8070438B2 (en) 2006-07-21 2011-12-06 Rolls-Royce Plc Fan blade for a gas turbine engine
US8287239B2 (en) 2008-03-07 2012-10-16 Rolls-Royce Plc Annulus filler
EP2108786A3 (en) * 2008-04-07 2012-12-26 Rolls-Royce plc Aeroengine fan assembly
US8425192B2 (en) 2009-05-18 2013-04-23 Rolls-Royce Plc Annulus filler
US8596981B2 (en) 2009-06-23 2013-12-03 Rolls-Royce Plc Annulus filler for a gas turbine engine
US8636474B2 (en) 2009-08-12 2014-01-28 Rolls-Royce Plc Rotor assembly for a gas turbine
US8864451B2 (en) 2010-03-23 2014-10-21 Rolls-Royce Plc Interstage seal
EP2932047A4 (en) * 2012-12-14 2015-12-09 United Technologies Corp Gas turbine engine fan blade platform seal
FR3052822A1 (en) * 2016-06-16 2017-12-22 Snecma TURBOMACHINE DAWN EQUIPPED WITH AN ELASTOMER SEAL
FR3093534A1 (en) * 2019-03-07 2020-09-11 Safran Aircraft Engines Aeronautical turbomachine fan platform
EP3851644A1 (en) * 2020-01-17 2021-07-21 Raytheon Technologies Corporation Turbine fan fairing platform with protective surface
CN114127425A (en) * 2019-06-26 2022-03-01 赛峰飞机发动机公司 Inter-blade platform with sacrificial box section

Cited By (33)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2654773A1 (en) * 1989-11-22 1991-05-24 Snecma AXIAL FLOW TURBOMACHINE ROTOR.
EP0429353A1 (en) * 1989-11-22 1991-05-29 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Axial turbomachine
US5145319A (en) * 1989-11-22 1992-09-08 Societe Nationale D'etude Et De Construction De Moteurs D'aviations S.N.E.M.C.A. Axial flow turbomachine rotor
GB2257755A (en) * 1991-07-17 1993-01-20 Snecma Interblade platform.
GB2257755B (en) * 1991-07-17 1994-07-20 Snecma Separate inter-blade platform for a bladed rotor disc
WO1993022539A1 (en) * 1992-05-07 1993-11-11 Rolls-Royce Plc Rotors for gas turbine engines
US5464326A (en) * 1992-05-07 1995-11-07 Rolls-Royce, Plc Rotors for gas turbine engines
FR2706528A1 (en) * 1993-06-10 1994-12-23 Snecma Separate inter-blade platform of turbine engine rotor blade disc.
EP0669451A1 (en) * 1994-02-23 1995-08-30 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Seal between the blades and the intermediate platforms
FR2716502A1 (en) * 1994-02-23 1995-08-25 Snecma Sealing between vanes and intermediate platforms.
US5520514A (en) * 1994-02-23 1996-05-28 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Sealing lining between vanes and intermediate platforms
EP0677645A1 (en) * 1994-03-19 1995-10-18 ROLLS-ROYCE plc A gas turbine engine fan blade assembly
US5580217A (en) * 1994-03-19 1996-12-03 Rolls-Royce Plc Gas turbine engine fan blade assembly
WO1997044570A1 (en) * 1996-05-20 1997-11-27 Pratt & Whitney Canada Inc. Gas turbine engine shroud seals
US8070438B2 (en) 2006-07-21 2011-12-06 Rolls-Royce Plc Fan blade for a gas turbine engine
US8287239B2 (en) 2008-03-07 2012-10-16 Rolls-Royce Plc Annulus filler
EP2108786A3 (en) * 2008-04-07 2012-12-26 Rolls-Royce plc Aeroengine fan assembly
US8535013B2 (en) 2008-04-07 2013-09-17 Rolls-Royce Plc Aeroengine fan assembly
US8425192B2 (en) 2009-05-18 2013-04-23 Rolls-Royce Plc Annulus filler
US8596981B2 (en) 2009-06-23 2013-12-03 Rolls-Royce Plc Annulus filler for a gas turbine engine
EP2267277A3 (en) * 2009-06-23 2017-11-29 Rolls-Royce plc Annulus filler and method of mounting the annulus filler to a rotor disc of a gas turbine engine
US8636474B2 (en) 2009-08-12 2014-01-28 Rolls-Royce Plc Rotor assembly for a gas turbine
US8864451B2 (en) 2010-03-23 2014-10-21 Rolls-Royce Plc Interstage seal
EP2932047A4 (en) * 2012-12-14 2015-12-09 United Technologies Corp Gas turbine engine fan blade platform seal
GB2552085A (en) * 2016-06-16 2018-01-10 Safran Aircraft Engines A turbine engine blade fitted with an elastomer gasket
FR3052822A1 (en) * 2016-06-16 2017-12-22 Snecma TURBOMACHINE DAWN EQUIPPED WITH AN ELASTOMER SEAL
US10689996B2 (en) 2016-06-16 2020-06-23 Safran Aircraft Engines Turbomachine blade fitted with an elastomer gasket
GB2552085B (en) * 2016-06-16 2020-11-11 Safran Aircraft Engines A turbomachine blade fitted with an elastomer gasket
FR3093534A1 (en) * 2019-03-07 2020-09-11 Safran Aircraft Engines Aeronautical turbomachine fan platform
CN114127425A (en) * 2019-06-26 2022-03-01 赛峰飞机发动机公司 Inter-blade platform with sacrificial box section
CN114127425B (en) * 2019-06-26 2023-08-29 赛峰飞机发动机公司 Inter-blade platform with sacrificial tank sections
EP3851644A1 (en) * 2020-01-17 2021-07-21 Raytheon Technologies Corporation Turbine fan fairing platform with protective surface
US11268396B2 (en) 2020-01-17 2022-03-08 Raytheon Technologies Corporation Turbine fan fairing platform with protective surface

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Legal Events

Date Code Title Description
PS Patent sealed
PLNP Patent lapsed through nonpayment of renewal fees