GB781771A - Improvements in or relating to axial-flow compressors and turbines - Google Patents

Improvements in or relating to axial-flow compressors and turbines

Info

Publication number
GB781771A
GB781771A GB23497/54A GB2349754A GB781771A GB 781771 A GB781771 A GB 781771A GB 23497/54 A GB23497/54 A GB 23497/54A GB 2349754 A GB2349754 A GB 2349754A GB 781771 A GB781771 A GB 781771A
Authority
GB
United Kingdom
Prior art keywords
platform members
rotor disc
platform
engage
projections
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
GB23497/54A
Inventor
Frederick William Walto Morley
Henry Cook
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
Priority to BE540433D priority Critical patent/BE540433A/xx
Application filed by Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB23497/54A priority patent/GB781771A/en
Priority to US523900A priority patent/US3008689A/en
Priority to FR1134548D priority patent/FR1134548A/en
Publication of GB781771A publication Critical patent/GB781771A/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
    • 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
    • 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
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F01D5/323—Locking of axial insertion type blades by means of a key or the like parallel to the axis of the rotor
    • 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
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F01D5/326—Locking of axial insertion type blades by other means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F22—STEAM GENERATION
    • F22B—METHODS OF STEAM GENERATION; STEAM BOILERS
    • F22B37/00—Component parts or details of steam boilers
    • F22B37/02—Component parts or details of steam boilers applicable to more than one kind or type of steam boiler
    • F22B37/42—Applications, arrangements, or dispositions of alarm or automatic safety devices

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

781,771. Turbine and compressor blade fixing. ROLLS-ROYCE, Ltd. Aug. 12, 1955 [Aug. 12, 1954], No. 23497/54. Class 110 (3). An axial-flow turbine or compressor has blades of the kind having a root-fixing portion 14, an aerofoil section blade portion proper 13 and an intermediate (or stem) portion 15 therebetween. According to the invention, separate platform members 18 are provided between pairs of adjacent blades to form the boundary of the working fluid passage therebetween and means are provided associated with each platform member to close off the space between the intermediate portions of adjacent blades so as to minimize the leakage of working fluid. The platform members are secured to the associated turbine or compressor structure by interengaging sliding features. In Fig. 1, the blade roots 14 are engaged in axial fir-tree section slots 11 formed in the rotor disc. The disc portions between the slots 11 are formed with T-section projections 17 and the inwardly-turned toes 20 of platform members 18 are engaged therewith. The platform members 18 are locked against axial movement and the spaces through the grooves 19 in the platform members are closed by means of plates 21 which engage grooves 22 in the rotor disc 10 and 23 in the platform members and which are prevented from dropping into the grooves 22 when in the operative position by engaging with the surfaces 24 on the adjacent blade roots. In a second modification, Figs. 5, 8, the platform members 18 have inwardly-turned toes 20 as before but are also formed with integral wall parts 25 which are of such circumferential length as to engage the intermediate portions 15 of the adjacent blades. The wall parts 25 close the passages between the intermediate portions of the blades and also prevent movement of the platform members from left to right, as seen in Fig. 8. Movement of the platform members in the other direction is prevented by means of locking-plates 26 which have central openings 30 which engage undercut lugs 28 formed on the rotor disc between blade root slots. The outer rim portions of the plates 26 engage circumferential grooves 27 formed on the under-surfaces of the platform members 18, while the inner rim portions 31 are bent into the groove 29 formed on the rotor disc, thereby retaining the locking- plate in position. In a third embodiment, Figs. 9, 10, the platform members 18 again have inwardly-turned toes 20 which engage T-shaped projections 17 on the rotor disc between the blade root slots. Each platform member is formed with a slot 50 terminating in a hole 51. A locking tab is engaged within the slot 50 and hole 51 and after assembly the end 53 of the locking tab is bent downwardly to engage the rearward face of the rotor disc 10 so as to prevent disengagement of the platform member in a forward direction. Disengagement in the opposite direction is prevented by means of a wall part 25 formed integrally with the platform member which engages with the forward face of the rotor disc. In a further embodiment, Figs. 11, 13, circumferentially-extending T-section projections 117 are formed on the rotor disc projections between the blade root slots, and the platform members 118 have inwardly-turned toes 120 which engage with the projections 117.
GB23497/54A 1954-08-12 1954-08-12 Improvements in or relating to axial-flow compressors and turbines Expired GB781771A (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
BE540433D BE540433A (en) 1954-08-12
GB23497/54A GB781771A (en) 1954-08-12 1954-08-12 Improvements in or relating to axial-flow compressors and turbines
US523900A US3008689A (en) 1954-08-12 1955-07-22 Axial-flow compressors and turbines
FR1134548D FR1134548A (en) 1954-08-12 1955-08-05 Compressors and turbines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB23497/54A GB781771A (en) 1954-08-12 1954-08-12 Improvements in or relating to axial-flow compressors and turbines

Publications (1)

Publication Number Publication Date
GB781771A true GB781771A (en) 1957-08-28

Family

ID=10196576

Family Applications (1)

Application Number Title Priority Date Filing Date
GB23497/54A Expired GB781771A (en) 1954-08-12 1954-08-12 Improvements in or relating to axial-flow compressors and turbines

Country Status (4)

Country Link
US (1) US3008689A (en)
BE (1) BE540433A (en)
FR (1) FR1134548A (en)
GB (1) GB781771A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1051286B (en) * 1958-06-02 1959-02-26 Her Majesty The Queen In The R Fuse for a blade held in an axial groove of a centrifugal machine
US5622476A (en) * 1994-12-14 1997-04-22 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Axial fixing arrangement for rotor blades of a turbomachine
DE19925774A1 (en) * 1999-06-05 2000-12-07 Asea Brown Boveri Rotor blades securement unit for axial-flow turbo-machine fits in radial space in axial grooves of rotor disc and is secured to blade foot and rotor by radially aligned sections of securing plate
US6561764B1 (en) * 1999-03-19 2003-05-13 Siemens Aktiengesellschaft Gas turbine rotor with an internally cooled gas turbine blade and connecting configuration including an insert strip bridging adjacent blade platforms

Families Citing this family (32)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3294364A (en) * 1962-01-02 1966-12-27 Gen Electric Rotor assembly
US3333818A (en) * 1965-03-22 1967-08-01 Gen Motors Corp Turbine rotor-jet nozzle assembly
CH494896A (en) * 1968-08-09 1970-08-15 Sulzer Ag Mounting of rotor blades in the rotor of a turbomachine
GB1318654A (en) * 1970-12-05 1973-05-31 Secr Defence Bladed rotors
BE794573A (en) * 1972-02-02 1973-05-16 Gen Electric AUBES FIXING DEVICE
US3801222A (en) * 1972-02-28 1974-04-02 United Aircraft Corp Platform for compressor or fan blade
US3841794A (en) * 1974-03-06 1974-10-15 United Aircraft Corp Snap-on lock for turbomachinery blades
GB1549422A (en) * 1976-10-19 1979-08-08 Rolls Royce Axial flow gas turbine engine compressor
FR2404134A1 (en) * 1977-09-23 1979-04-20 Snecma ROTOR FOR TURBOMACHINES
JPS5848728B2 (en) * 1979-03-30 1983-10-31 川崎重工業株式会社 Seal structure between turbine blades
FR2503247B1 (en) * 1981-04-07 1985-06-14 Snecma IMPROVEMENTS ON THE FLOORS OF A GAS TURBINE OF TURBOREACTORS PROVIDED WITH AIR COOLING MEANS OF THE TURBINE WHEEL DISC
GB2171151B (en) * 1985-02-20 1988-05-18 Rolls Royce Rotors for gas turbine engines
FR2608674B1 (en) * 1986-12-17 1991-04-19 Snecma CERAMIC BLADE TURBINE WHEEL
DE3743253A1 (en) * 1987-12-19 1989-06-29 Mtu Muenchen Gmbh AXIAL FLOWED BLADE BLADES FOR COMPRESSORS OR TURBINES
US4813850A (en) * 1988-04-06 1989-03-21 Westinghouse Electric Corp. Integral side entry control stage blade group
FR2639402B1 (en) * 1988-11-23 1990-12-28 Snecma TURBOMACHINE ROTOR WING DISC
US5001830A (en) * 1989-10-23 1991-03-26 Westinghouse Electric Corp. Method for assembling side entry control stage blades in a steam turbine
FR2669686B1 (en) * 1990-11-28 1994-09-02 Snecma BLOWER ROTOR WITH BLADES WITHOUT PLATFORMS AND SHOES RECONSTRUCTING THE VEIN PROFILE.
GB2251897B (en) * 1991-01-15 1994-11-30 Rolls Royce Plc A rotor
GB9405473D0 (en) * 1994-03-19 1994-05-04 Rolls Royce Plc A gas turbine engine fan blade assembly
WO2000057032A1 (en) * 1999-03-24 2000-09-28 Siemens Aktiengesellschaft Guide blade and guide blade rim for a fluid-flow machine and component for delimiting a flow channel
US7284958B2 (en) * 2003-03-22 2007-10-23 Allison Advanced Development Company Separable blade platform
US7604456B2 (en) * 2006-04-11 2009-10-20 Siemens Energy, Inc. Vane shroud through-flow platform cover
US7931442B1 (en) * 2007-05-31 2011-04-26 Florida Turbine Technologies, Inc. Rotor blade assembly with de-coupled composite platform
FR2918409B1 (en) * 2007-07-05 2011-05-27 Snecma ROTATING PART OF TURBOMACHINE COMPRISING INTER-AUB SECTIONS FORMING PLATFORM FIXED ON A DISK
US8277190B2 (en) * 2009-03-27 2012-10-02 General Electric Company Turbomachine rotor assembly and method
FR2961847B1 (en) * 2010-06-25 2012-08-17 Snecma AUBES MOBILE WHEEL IN COMPOSITE MATERIAL FOR A TURBINE GAS TURBINE ENGINE WITH A WAVEBASE / TIGHTENING DISC
CH704825A1 (en) 2011-03-31 2012-10-15 Alstom Technology Ltd Turbomachinery rotor.
WO2015038605A1 (en) 2013-09-12 2015-03-19 United Technologies Corporation Disk outer rim seal
US9896946B2 (en) * 2013-10-31 2018-02-20 General Electric Company Gas turbine engine rotor assembly and method of assembling the same
US9920627B2 (en) * 2014-05-22 2018-03-20 United Technologies Corporation Rotor heat shield
CN109209995B (en) * 2017-06-30 2020-04-28 中国航发商用航空发动机有限责任公司 Axial flow compressor

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1585713A (en) * 1922-05-31 1926-05-25 Westinghouse Electric & Mfg Co Turbine-blade fastening
FR969413A (en) * 1948-07-20 1950-12-20 Const Et D Equipements Ments M Further training in the construction and fixing of hollow blades for gas turbines
FR989556A (en) * 1949-06-25 1951-09-11 Cem Comp Electro Mec Improvement in turbo-machine blades
GB687507A (en) * 1949-06-28 1953-02-18 Cem Comp Electro Mec Improvements in turbine and compressor blades
GB671960A (en) * 1949-08-23 1952-05-14 Bristol Aeroplane Co Ltd Improvements in or relating to attachment means for rotor blades
FR998221A (en) * 1949-10-26 1952-01-16 Soc D Const Et D Equipements M Improvements in the attachment of turbo-machine blades
US2751189A (en) * 1950-09-08 1956-06-19 United Aircraft Corp Blade fastening means
GB699582A (en) * 1950-11-14 1953-11-11 Rolls Royce Improvements in or relating to gas-turbine engines
US2669383A (en) * 1951-02-06 1954-02-16 A V Roe Canada Ltd Rotor blade

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1051286B (en) * 1958-06-02 1959-02-26 Her Majesty The Queen In The R Fuse for a blade held in an axial groove of a centrifugal machine
US5622476A (en) * 1994-12-14 1997-04-22 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Axial fixing arrangement for rotor blades of a turbomachine
US6561764B1 (en) * 1999-03-19 2003-05-13 Siemens Aktiengesellschaft Gas turbine rotor with an internally cooled gas turbine blade and connecting configuration including an insert strip bridging adjacent blade platforms
DE19925774A1 (en) * 1999-06-05 2000-12-07 Asea Brown Boveri Rotor blades securement unit for axial-flow turbo-machine fits in radial space in axial grooves of rotor disc and is secured to blade foot and rotor by radially aligned sections of securing plate

Also Published As

Publication number Publication date
US3008689A (en) 1961-11-14
FR1134548A (en) 1957-04-12
BE540433A (en)

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