GB2006883A - Fan or Compressor Rotor Stage - Google Patents

Fan or Compressor Rotor Stage

Info

Publication number
GB2006883A
GB2006883A GB7841514A GB7841514A GB2006883A GB 2006883 A GB2006883 A GB 2006883A GB 7841514 A GB7841514 A GB 7841514A GB 7841514 A GB7841514 A GB 7841514A GB 2006883 A GB2006883 A GB 2006883A
Authority
GB
United Kingdom
Prior art keywords
fan
spacer
engaging
compressor rotor
rotor stage
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.)
Granted
Application number
GB7841514A
Other versions
GB2006883B (en
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
Priority to GB7841514A priority Critical patent/GB2006883B/en
Publication of GB2006883A publication Critical patent/GB2006883A/en
Application granted granted Critical
Publication of GB2006883B publication Critical patent/GB2006883B/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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
    • 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)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The stage comprises a rotor disc (12) from the periphery of which a row of angularly spaced apart rotor blades (13) is carried. To define the inner boundary of the flow passage through the stage, spacers (16) are provided between adjacent blades (13). Each spacer (16) has a rearward extremity (18) engaging the inward facing groove (19) of a thrust ring (20), and a forward extremity (23) engaging the forward face (24) of the disc to prevent rearward motion of the spacer. A recess 25 in the latter is engaged by retaining ring 27. <IMAGE>
GB7841514A 1977-10-27 1978-10-23 Fan or compressor stage for a gas turbine engine Expired GB2006883B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB7841514A GB2006883B (en) 1977-10-27 1978-10-23 Fan or compressor stage for a gas turbine engine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB4466677 1977-10-27
GB7841514A GB2006883B (en) 1977-10-27 1978-10-23 Fan or compressor stage for a gas turbine engine

Publications (2)

Publication Number Publication Date
GB2006883A true GB2006883A (en) 1979-05-10
GB2006883B GB2006883B (en) 1982-02-24

Family

ID=26265436

Family Applications (1)

Application Number Title Priority Date Filing Date
GB7841514A Expired GB2006883B (en) 1977-10-27 1978-10-23 Fan or compressor stage for a gas turbine engine

Country Status (1)

Country Link
GB (1) GB2006883B (en)

Cited By (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4655687A (en) * 1985-02-20 1987-04-07 Rolls-Royce Rotors for gas turbine engines
FR2639402A1 (en) * 1988-11-23 1990-05-25 Snecma TURBOMACHINE ROTOR WING DISC
US5030063A (en) * 1990-02-08 1991-07-09 General Motors Corporation Turbomachine rotor
FR2669686A1 (en) * 1990-11-28 1992-05-29 Snecma BLOWER ROTOR WITH BLADES WITHOUT PLATFORMS AND SHOES RECONSTRUCTING THE VEIN PROFILE.
EP0502660A1 (en) * 1991-03-04 1992-09-09 General Electric Company Platform assembly for attaching rotor blades to a rotor disk
GB2257755A (en) * 1991-07-17 1993-01-20 Snecma Interblade platform.
US5222865A (en) * 1991-03-04 1993-06-29 General Electric Company Platform assembly for attaching rotor blades to a rotor disk
US5232346A (en) * 1992-08-11 1993-08-03 General Electric Company Rotor assembly and platform spacer therefor
US5244345A (en) * 1991-01-15 1993-09-14 Rolls-Royce Plc Rotor
WO1993021425A1 (en) * 1992-04-16 1993-10-28 Rolls-Royce Plc Rotors for gas turbine engines
US5277548A (en) * 1991-12-31 1994-01-11 United Technologies Corporation Non-integral rotor blade platform
US5281096A (en) * 1992-09-10 1994-01-25 General Electric Company Fan assembly having lightweight platforms
US5330324A (en) * 1992-09-09 1994-07-19 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Annular gasket disposed at one axial extremity of a rotor and covering blade feet
WO1994016200A1 (en) * 1993-01-12 1994-07-21 United Technologies Corporation Free standing turbine disk sideplate assembly
FR2706528A1 (en) * 1993-06-10 1994-12-23 Snecma Separate inter-blade platform of turbine engine rotor blade disc.
FR2710103A1 (en) * 1993-09-16 1995-03-24 Snecma Turbomachine rotor flange and assembly of this flange to a rotor
FR2715975A1 (en) * 1994-02-10 1995-08-11 Snecma Rotor turbine rotor with axial or inclined emergent blade grooves.
EP0677645A1 (en) * 1994-03-19 1995-10-18 ROLLS-ROYCE plc A gas turbine engine fan blade assembly
US6217283B1 (en) * 1999-04-20 2001-04-17 General Electric Company Composite fan platform
WO2001059263A2 (en) * 2000-02-09 2001-08-16 Siemens Aktiengesellschaft Turbine blade arrangement
FR2965843A1 (en) * 2010-10-06 2012-04-13 Snecma ROTOR FOR TURBOMACHINE
US8292586B2 (en) 2008-02-18 2012-10-23 Rolls-Royce Plc Annulus filler
US8777576B2 (en) 2011-08-22 2014-07-15 General Electric Company Metallic fan blade platform
JP2019512639A (en) * 2016-03-21 2019-05-16 サフラン エアークラフト エンジンズ Wing pedestal and fan disk for aircraft turbine engines
US20190218912A1 (en) * 2018-01-16 2019-07-18 Rolls-Royce Plc Annulus filler
WO2019224464A1 (en) * 2018-05-23 2019-11-28 Safran Aircraft Engines Improved turbmachine fan disc
EP4353952A1 (en) * 2022-10-14 2024-04-17 RTX Corporation Retention of a fan blade of a gas turbine engine

Cited By (46)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4655687A (en) * 1985-02-20 1987-04-07 Rolls-Royce Rotors for gas turbine engines
FR2639402A1 (en) * 1988-11-23 1990-05-25 Snecma TURBOMACHINE ROTOR WING DISC
EP0370899A1 (en) * 1988-11-23 1990-05-30 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Turbine-bladed rotor disc
US5049035A (en) * 1988-11-23 1991-09-17 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Bladed disc for a turbomachine rotor
US5030063A (en) * 1990-02-08 1991-07-09 General Motors Corporation Turbomachine rotor
EP0441424A1 (en) * 1990-02-08 1991-08-14 General Motors Corporation Turbomachine rotor
US5161949A (en) * 1990-11-28 1992-11-10 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.M.C.A." Rotor fitted with spacer blocks between the blades
FR2669686A1 (en) * 1990-11-28 1992-05-29 Snecma BLOWER ROTOR WITH BLADES WITHOUT PLATFORMS AND SHOES RECONSTRUCTING THE VEIN PROFILE.
EP0488874A1 (en) * 1990-11-28 1992-06-03 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Fan rotor with blades without platforms and fillers reconstructing the streamline profile
US5244345A (en) * 1991-01-15 1993-09-14 Rolls-Royce Plc Rotor
US5222865A (en) * 1991-03-04 1993-06-29 General Electric Company Platform assembly for attaching rotor blades to a rotor disk
EP0502660A1 (en) * 1991-03-04 1992-09-09 General Electric Company Platform assembly for attaching rotor blades to a rotor disk
FR2679296A1 (en) * 1991-07-17 1993-01-22 Snecma SEPARATE INTER-BEAM PLATFORM FOR ROTOR TURBOMACHINE ROTOR DISC.
US5193982A (en) * 1991-07-17 1993-03-16 Societe Nationale D'etude Et De Construction De Moteurs D'aviation S.N.E.C.M.A. Separate inter-blade platform for a bladed rotor disk
GB2257755B (en) * 1991-07-17 1994-07-20 Snecma Separate inter-blade platform for a bladed rotor disc
GB2257755A (en) * 1991-07-17 1993-01-20 Snecma Interblade platform.
US5277548A (en) * 1991-12-31 1994-01-11 United Technologies Corporation Non-integral rotor blade platform
WO1993021425A1 (en) * 1992-04-16 1993-10-28 Rolls-Royce Plc Rotors for gas turbine engines
US5466125A (en) * 1992-04-16 1995-11-14 Rolls-Royce Plc Rotors for gas turbine engines
US5232346A (en) * 1992-08-11 1993-08-03 General Electric Company Rotor assembly and platform spacer therefor
US5330324A (en) * 1992-09-09 1994-07-19 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Annular gasket disposed at one axial extremity of a rotor and covering blade feet
US5281096A (en) * 1992-09-10 1994-01-25 General Electric Company Fan assembly having lightweight platforms
WO1994016200A1 (en) * 1993-01-12 1994-07-21 United Technologies Corporation Free standing turbine disk sideplate assembly
FR2706528A1 (en) * 1993-06-10 1994-12-23 Snecma Separate inter-blade platform of turbine engine rotor blade disc.
US5421704A (en) * 1993-06-10 1995-06-06 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Inter-blade platform for a bladed disc of a turbomachine rotor
FR2710103A1 (en) * 1993-09-16 1995-03-24 Snecma Turbomachine rotor flange and assembly of this flange to a rotor
FR2715975A1 (en) * 1994-02-10 1995-08-11 Snecma Rotor turbine rotor with axial or inclined emergent blade grooves.
US5540552A (en) * 1994-02-10 1996-07-30 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Turbine engine rotor having axial or inclined, issuing blade grooves
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
US6217283B1 (en) * 1999-04-20 2001-04-17 General Electric Company Composite fan platform
US6726452B2 (en) 2000-02-09 2004-04-27 Siemens Aktiengesellschaft Turbine blade arrangement
EP1124038A1 (en) * 2000-02-09 2001-08-16 Siemens Aktiengesellschaft Turbine blading
WO2001059263A3 (en) * 2000-02-09 2002-09-19 Siemens Ag Turbine blade arrangement
WO2001059263A2 (en) * 2000-02-09 2001-08-16 Siemens Aktiengesellschaft Turbine blade arrangement
US8292586B2 (en) 2008-02-18 2012-10-23 Rolls-Royce Plc Annulus filler
FR2965843A1 (en) * 2010-10-06 2012-04-13 Snecma ROTOR FOR TURBOMACHINE
US8777576B2 (en) 2011-08-22 2014-07-15 General Electric Company Metallic fan blade platform
JP2019512639A (en) * 2016-03-21 2019-05-16 サフラン エアークラフト エンジンズ Wing pedestal and fan disk for aircraft turbine engines
US20190218912A1 (en) * 2018-01-16 2019-07-18 Rolls-Royce Plc Annulus filler
WO2019224464A1 (en) * 2018-05-23 2019-11-28 Safran Aircraft Engines Improved turbmachine fan disc
FR3081520A1 (en) * 2018-05-23 2019-11-29 Safran Aircraft Engines IMPROVED TURBOMACHINE BLOWER DISK
CN112189097A (en) * 2018-05-23 2021-01-05 赛峰飞机发动机公司 Improved turbine fan disk
US11313239B2 (en) 2018-05-23 2022-04-26 Safran Aircraft Engines Turbmachine fan disc
EP4353952A1 (en) * 2022-10-14 2024-04-17 RTX Corporation Retention of a fan blade of a gas turbine engine
US12012857B2 (en) 2022-10-14 2024-06-18 Rtx Corporation Platform for an airfoil of a gas turbine engine

Also Published As

Publication number Publication date
GB2006883B (en) 1982-02-24

Similar Documents

Publication Publication Date Title
GB2006883A (en) Fan or Compressor Rotor Stage
GB1286776A (en) Bladed rotors for turbomachines
GB1479332A (en) Means for retaining blades to a disc or like structure
SE8008936L (en) TURBIN LEAD COVER SUSPENSION FOR GAS TURBINE ENGINES
SE8107451L (en) LOADING OF ROTOR BLADES
SE8400381L (en) DEVICE FOR PRESSURIZER FOR LIQUID
GB831412A (en) Improvements relating to axial-flow turbines
SE8601834D0 (en) HYDRAULIC TORQUE IMPULSE GENERATOR WITH BYPASS MEANS
FR2448049A1 (en) Vertical wind turbine coupled to pump or electricity generator - with stator plates around rotor ensuring rotation independent of wind direction
JPS53137407A (en) Centrifugal compressor for gas turbine
GB2010404A (en) Cooling Turbine Rotor Blades
GB1364120A (en) Axial flow compressors
JPS5364112A (en) Gas turbine compressor
FR2375440A1 (en) Rotor of axial flow steam turbine - has shroud ring round blade tips with slots to give tangential elasticity
GB1417154A (en) Compressor intakes
GB1339485A (en) Turbine or compressor rotors
IT963706B (en) THRUST VARIATORS FOR DUCTED FAN GAS TURBINE ENGINES
JPS53141851A (en) Step shaft
GB1390502A (en) High speed gas driven turbines
SU487588A1 (en) Turbine drill
JPS5429102A (en) Impeller of pump with high water head
IT7851882A0 (en) IMPROVEMENT IN DRIVE SYSTEMS FOR GAS TURBINE ENGINES WITH DISC REGENERATORS
JPS5236242A (en) Closed generating set
SU879024A1 (en) Roller-blade hydraulic machine
JPS5413004A (en) Vane wheel of linear radial inclined flow fan

Legal Events

Date Code Title Description
PCNP Patent ceased through non-payment of renewal fee