US3008689A - Axial-flow compressors and turbines - Google Patents

Axial-flow compressors and turbines Download PDF

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Publication number
US3008689A
US3008689A US523900A US52390055A US3008689A US 3008689 A US3008689 A US 3008689A US 523900 A US523900 A US 523900A US 52390055 A US52390055 A US 52390055A US 3008689 A US3008689 A US 3008689A
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US
United States
Prior art keywords
platform
disc
groove
blades
blade
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 - Lifetime
Application number
US523900A
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English (en)
Inventor
Morley Frederick Willia Walton
Cook Henry
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
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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 US3008689A publication Critical patent/US3008689A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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    • 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

Definitions

  • FIGURE 8 is a section on the line VII-VIII of FIG- URE 6.
  • FIGURE 11 is a view corresponding to FIGURE 1 of a fourth embodiment
  • FIGURE 12 is a developed plan view of FIGURE 11, partly in section, and
  • the length of the platforms 118 measured in the circumferential direction is slightly less than the distance between the adjacent ends of neighbouring formations 117, so that each platform 118 can be entered in the open end of a fir-tree groove 11 and engaged with the co-operating formation 117 by a circumferential movement. It is arranged that the platform member 118 is moved circumferentially into engagement with the intermediate portion 15 of a previously inserted blade, and that this movement permits the next adjacent blade to be inserted in its groove 11 on the other side of the plaform 118. The next platform 118 may then be assembled and so on.
  • a rotor as claimed in claim 9 in which the T-shaped formations extend across said rotor disc member from its forward face to its rear face, so that the platform members are slid on to the said T-shaped formations in a direction substantially axial of the rotor disc member.
  • a rotor as claimed in claim 9 in which the T-shaped formation extend substantially circumferentially of the rotor disc member and lie between blade root interengaging slots, and the spaces between adjacent T-shaped formations are suflieient to allow the platform members to be entered into the said spaces and then moved substan tially circumferenitally of the rotor disc member to engage one of said T-shaped formations.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US523900A 1954-08-12 1955-07-22 Axial-flow compressors and turbines Expired - Lifetime US3008689A (en)

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
US3008689A true US3008689A (en) 1961-11-14

Family

ID=10196576

Family Applications (1)

Application Number Title Priority Date Filing Date
US523900A Expired - Lifetime US3008689A (en) 1954-08-12 1955-07-22 Axial-flow compressors and turbines

Country Status (4)

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

Cited By (30)

* 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
US3610778A (en) * 1968-08-09 1971-10-05 Sulzer Ag Support for rotor blades in a rotor
US3734646A (en) * 1972-02-02 1973-05-22 Gen Electric Blade fastening means
US3761200A (en) * 1970-12-05 1973-09-25 Secr Defence Bladed rotors
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
US4175912A (en) * 1976-10-19 1979-11-27 Rolls-Royce Limited Axial flow gas turbine engine compressor
JPS55131503A (en) * 1979-03-30 1980-10-13 Kawasaki Heavy Ind Ltd Seal structure between turbine blades
US4277225A (en) * 1977-09-23 1981-07-07 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Rotor for jet engines
US4457668A (en) * 1981-04-07 1984-07-03 S.N.E.C.M.A. Gas turbine stages of turbojets with devices for the air cooling of the turbine wheel disc
US4655687A (en) * 1985-02-20 1987-04-07 Rolls-Royce Rotors for gas turbine engines
US4802824A (en) * 1986-12-17 1989-02-07 Societe Nationale D'etude Et Moteurs D'aviation "S.N.E.C.M.A." Turbine rotor
US4813850A (en) * 1988-04-06 1989-03-21 Westinghouse Electric Corp. Integral side entry control stage blade group
US5001830A (en) * 1989-10-23 1991-03-26 Westinghouse Electric Corp. Method for assembling side entry control stage blades in a steam turbine
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
US5244345A (en) * 1991-01-15 1993-09-14 Rolls-Royce Plc Rotor
US5580217A (en) * 1994-03-19 1996-12-03 Rolls-Royce Plc Gas turbine engine fan blade assembly
WO2000057032A1 (de) * 1999-03-24 2000-09-28 Siemens Aktiengesellschaft Leitschaufel und leitschaufelkranz für eine strömungsmaschine, sowie bauteil zur begrenzung eines strömungskanals
US20070189901A1 (en) * 2003-03-22 2007-08-16 Dundas Jason E Separable blade platform
US20070237630A1 (en) * 2006-04-11 2007-10-11 Siemens Power Generation, Inc. Vane shroud through-flow platform cover
FR2918409A1 (fr) * 2007-07-05 2009-01-09 Snecma Sa Partie tournante de turbomachine comprenant des secteurs inter-aubes formant plateforme rapportes fixement sur un disque
CN101845970A (zh) * 2009-03-27 2010-09-29 通用电气公司 涡轮机转子组件和方法
US7931442B1 (en) * 2007-05-31 2011-04-26 Florida Turbine Technologies, Inc. Rotor blade assembly with de-coupled composite platform
JP2012215175A (ja) * 2011-03-31 2012-11-08 Alstom Technology Ltd ターボ機械モータ
US20130156590A1 (en) * 2010-06-25 2013-06-20 Snecma Gas turbine engine rotor wheel having composite material blades with blade-root to disk connection being obtained by clamping
US20150118055A1 (en) * 2013-10-31 2015-04-30 General Electric Company Gas turbine engine rotor assembly and method of assembling the same
US20160376892A1 (en) * 2014-05-22 2016-12-29 United Technologies Corporation Rotor heat shield
US10167722B2 (en) 2013-09-12 2019-01-01 United Technologies Corporation Disk outer rim seal
CN109209995A (zh) * 2017-06-30 2019-01-15 中国航发商用航空发动机有限责任公司 轴流压气机

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1051286B (de) * 1958-06-02 1959-02-26 Her Majesty The Queen In The R Sicherung fuer eine in einer Axialnut einer Kreiselmaschine gehaltene Schaufel
DE3743253A1 (de) * 1987-12-19 1989-06-29 Mtu Muenchen Gmbh Axial durchstroemtes laufschaufelgitter fuer verdichter oder turbinen
FR2669686B1 (fr) * 1990-11-28 1994-09-02 Snecma Rotor de soufflante avec aubes sans plates-formes et sabots reconstituant le profil de veine.
FR2728299B1 (fr) * 1994-12-14 1997-01-24 Snecma Dispositif de fixation axiale d'aubes de rotor de turboreacteur
WO2000057031A1 (de) * 1999-03-19 2000-09-28 Siemens Aktiengesellschaft Gasturbinenrotor mit innenraumgekühlter gasturbinenschaufel
DE19925774A1 (de) * 1999-06-05 2000-12-07 Asea Brown Boveri Axiale Sicherungseinrichtung für Laufschaufeln axial durchströmter Turbomaschinen

Citations (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 (fr) * 1948-07-20 1950-12-20 Const Et D Equipements Ments M Perfectionnement dans la construction et la fixation des aubes creuses pour turbinesà gaz
FR989556A (fr) * 1949-06-25 1951-09-11 Cem Comp Electro Mec Perfectionnement aux aubes de turbo-machines
FR998221A (fr) * 1949-10-26 1952-01-16 Soc D Const Et D Equipements M Perfectionnements dans la fixation des aubes de turbo-machines
GB671960A (en) * 1949-08-23 1952-05-14 Bristol Aeroplane Co Ltd Improvements in or relating to attachment means for rotor blades
GB687507A (en) * 1949-06-28 1953-02-18 Cem Comp Electro Mec Improvements in turbine and compressor blades
US2669383A (en) * 1951-02-06 1954-02-16 A V Roe Canada Ltd Rotor blade
US2751189A (en) * 1950-09-08 1956-06-19 United Aircraft Corp Blade fastening means
US2755063A (en) * 1950-11-14 1956-07-17 Rolls Royce Rotor constructions for gas-turbine engines

Patent Citations (10)

* 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 (fr) * 1948-07-20 1950-12-20 Const Et D Equipements Ments M Perfectionnement dans la construction et la fixation des aubes creuses pour turbinesà gaz
FR59398E (fr) * 1948-07-20 1954-05-25 Const Et D Equipements Mecaniq Perfectionnements dans la construction et la fixation des aubes creuses pour turbines à gaz
FR989556A (fr) * 1949-06-25 1951-09-11 Cem Comp Electro Mec Perfectionnement aux aubes de turbo-machines
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 (fr) * 1949-10-26 1952-01-16 Soc D Const Et D Equipements M Perfectionnements dans la fixation des aubes de turbo-machines
US2751189A (en) * 1950-09-08 1956-06-19 United Aircraft Corp Blade fastening means
US2755063A (en) * 1950-11-14 1956-07-17 Rolls Royce Rotor constructions for gas-turbine engines
US2669383A (en) * 1951-02-06 1954-02-16 A V Roe Canada Ltd Rotor blade

Cited By (40)

* 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
US3610778A (en) * 1968-08-09 1971-10-05 Sulzer Ag Support for rotor blades in a rotor
US3761200A (en) * 1970-12-05 1973-09-25 Secr Defence Bladed rotors
US3734646A (en) * 1972-02-02 1973-05-22 Gen Electric Blade fastening means
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
US4175912A (en) * 1976-10-19 1979-11-27 Rolls-Royce Limited Axial flow gas turbine engine compressor
US4277225A (en) * 1977-09-23 1981-07-07 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Rotor for jet engines
JPS55131503A (en) * 1979-03-30 1980-10-13 Kawasaki Heavy Ind Ltd Seal structure between turbine blades
US4457668A (en) * 1981-04-07 1984-07-03 S.N.E.C.M.A. Gas turbine stages of turbojets with devices for the air cooling of the turbine wheel disc
US4655687A (en) * 1985-02-20 1987-04-07 Rolls-Royce Rotors for gas turbine engines
US4802824A (en) * 1986-12-17 1989-02-07 Societe Nationale D'etude Et Moteurs D'aviation "S.N.E.C.M.A." Turbine rotor
US4813850A (en) * 1988-04-06 1989-03-21 Westinghouse Electric Corp. Integral side entry control stage blade group
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
US5001830A (en) * 1989-10-23 1991-03-26 Westinghouse Electric Corp. Method for assembling side entry control stage blades in a steam turbine
US5244345A (en) * 1991-01-15 1993-09-14 Rolls-Royce Plc Rotor
US5580217A (en) * 1994-03-19 1996-12-03 Rolls-Royce Plc Gas turbine engine fan blade assembly
WO2000057032A1 (de) * 1999-03-24 2000-09-28 Siemens Aktiengesellschaft Leitschaufel und leitschaufelkranz für eine strömungsmaschine, sowie bauteil zur begrenzung eines strömungskanals
US6632070B1 (en) 1999-03-24 2003-10-14 Siemens Aktiengesellschaft Guide blade and guide blade ring for a turbomachine, and also component for bounding a flow duct
US20070189901A1 (en) * 2003-03-22 2007-08-16 Dundas Jason E Separable blade platform
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
US20070237630A1 (en) * 2006-04-11 2007-10-11 Siemens Power Generation, 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
FR2918409A1 (fr) * 2007-07-05 2009-01-09 Snecma Sa Partie tournante de turbomachine comprenant des secteurs inter-aubes formant plateforme rapportes fixement sur un disque
EP2233696A3 (en) * 2009-03-27 2013-03-06 General Electric Company Turbomachine rotor assembly and method
CN101845970A (zh) * 2009-03-27 2010-09-29 通用电气公司 涡轮机转子组件和方法
US8591192B2 (en) 2009-03-27 2013-11-26 General Electric Company Turbomachine rotor assembly and method
JP2010230007A (ja) * 2009-03-27 2010-10-14 General Electric Co <Ge> ターボ機械のロータ組立体とその組立方法
US20130156590A1 (en) * 2010-06-25 2013-06-20 Snecma Gas turbine engine rotor wheel having composite material blades with blade-root to disk connection being obtained by clamping
US9422818B2 (en) * 2010-06-25 2016-08-23 Snecma Gas turbine engine rotor wheel having composite material blades with blade-root to disk connection being obtained by clamping
JP2012215175A (ja) * 2011-03-31 2012-11-08 Alstom Technology Ltd ターボ機械モータ
US8915716B2 (en) 2011-03-31 2014-12-23 Alstom Technology Ltd. Turbomachine rotor
US10167722B2 (en) 2013-09-12 2019-01-01 United Technologies Corporation Disk outer rim seal
US20150118055A1 (en) * 2013-10-31 2015-04-30 General Electric Company Gas turbine engine rotor assembly and method of assembling the same
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
US20160376892A1 (en) * 2014-05-22 2016-12-29 United Technologies Corporation Rotor heat shield
CN109209995A (zh) * 2017-06-30 2019-01-15 中国航发商用航空发动机有限责任公司 轴流压气机

Also Published As

Publication number Publication date
GB781771A (en) 1957-08-28
FR1134548A (fr) 1957-04-12
BE540433A (enrdf_load_stackoverflow)

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