GB1313938A - Gas turbine engines - Google Patents

Gas turbine engines

Info

Publication number
GB1313938A
GB1313938A GB3791770A GB3791770A GB1313938A GB 1313938 A GB1313938 A GB 1313938A GB 3791770 A GB3791770 A GB 3791770A GB 3791770 A GB3791770 A GB 3791770A GB 1313938 A GB1313938 A GB 1313938A
Authority
GB
United Kingdom
Prior art keywords
turbine
shaft
blades
journal
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
Application number
GB3791770A
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.)
Bennes Marrel SA
Original Assignee
Bennes Marrel SA
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 Bennes Marrel SA filed Critical Bennes Marrel SA
Publication of GB1313938A publication Critical patent/GB1313938A/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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Supercharger (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Support Of The Bearing (AREA)

Abstract

1313938 Turbines; gas turbine plant BENNES MARREL 6 Aug 1970 [14 Aug 1969] 37917/70 Headings FIG and F1T In a gas turbine engine having angularly adjust-. able stator blades 16 disposed between a compressor driving turbine 2 and a power turbine 4 each blade 16 is integral with a journal 17 and a shaft 18, the latter carrying a pinion 19 meshing with a gear ring 33 for adjusting the blades. The journal 17 and shaft 18 are mounted in bearings 24, 25 housed in an extension 26 of turbine casing 23, bearing 25 being held in position by a circlip (30), Fig. 4 (not shown). The ends 20, 21 of each blade 16 and the adjacent casing parts 22, 23 have a part spherical profile. A spring (29) surrounds shaft 18 and at its lower end bears against a washer (28) in contact with the step between journal 17 and shaft 18 so as to urge the blade end 20 into sealing contact with part 22. Gear ring 33 is mounted on ball or roller races and its angular movement is effected by a hydraulically operated piston and cylinder device (41, 42) Fig. 5 (not shown). Upstream of guide blades 16 is disposed an array of struts 14 supporting a casing part 55, the struts having cooling air passages 48. Turbine 2 drives a centrifugal compressor (1), Fig. 1, 2 (not shown) which supplies air through rotary regenerators (10) to combustion chambers (12). The engine may drive a road vehicle in which case the blades 16 can be moved into position in which the combustion gases effect a braking action on turbine 4.
GB3791770A 1969-08-14 1970-08-06 Gas turbine engines Expired GB1313938A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR6928154A FR2055780A1 (en) 1969-08-14 1969-08-14

Publications (1)

Publication Number Publication Date
GB1313938A true GB1313938A (en) 1973-04-18

Family

ID=9039087

Family Applications (1)

Application Number Title Priority Date Filing Date
GB3791770A Expired GB1313938A (en) 1969-08-14 1970-08-06 Gas turbine engines

Country Status (12)

Country Link
US (1) US3685921A (en)
AT (1) AT309913B (en)
CA (1) CA940051A (en)
CH (1) CH520267A (en)
CS (1) CS149924B2 (en)
DE (1) DE2039064C3 (en)
ES (1) ES382608A1 (en)
FR (1) FR2055780A1 (en)
GB (1) GB1313938A (en)
NL (1) NL7012074A (en)
SE (1) SE360425B (en)
ZA (1) ZA705605B (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2206381A (en) * 1987-06-30 1989-01-05 Rolls Royce Plc A variable stator vane arrangement for a compressor

Families Citing this family (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA1034509A (en) * 1975-10-14 1978-07-11 John Korta Vane rotator assembly for a gas turbine
CA1052231A (en) * 1976-04-22 1979-04-10 Dominion Engineering Works Limited Water turbine bearing seal
US4150915A (en) * 1976-12-23 1979-04-24 Caterpillar Tractor Co. Variable geometry turbine nozzle
DE2835349C2 (en) * 1978-08-11 1979-12-20 Mtu Motoren- Und Turbinen-Union Muenchen Gmbh, 8000 Muenchen Adjustable grille for highly loaded compressors, especially of gas turbine engines
DE2931766C2 (en) * 1979-08-04 1982-08-05 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Sealing device for the free blade ends of an adjustable diffuser of a gas turbine
FR2599785B1 (en) * 1986-06-04 1990-10-12 Snecma VARIABLE SETTING AIR INTAKE DIRECTOR FOR TURBOJET
DE4100224C2 (en) * 1991-01-07 1994-05-19 Daimler Benz Ag Mounting a gas turbine diffuser in a turbine housing
DE4213716A1 (en) * 1992-04-25 1993-10-28 Asea Brown Boveri Turbine with direct axial flow - has guide blades, which are axially movable in adjusting axis
US6394766B1 (en) * 1999-11-01 2002-05-28 James G. Gill Fan with adjustable guide vanes
FR2814205B1 (en) 2000-09-18 2003-02-28 Snecma Moteurs IMPROVED FLOW VEIN TURBOMACHINE
ITTO20010445A1 (en) * 2001-05-11 2002-11-11 Fiatavio Spa STATOR OF A VARIABLE GEOMETRY AXIAL TURBINE FOR AIRCRAFT APPLICATIONS.
DE10311205B3 (en) * 2003-03-14 2004-09-16 Man B & W Diesel Ag Guiding device for a radial turbine of a turbocharger of a lifting piston I.C. engine operating with heavy oil has blades with shafts positioned in a housing part of the device facing a compressor of the turbocharger
ITMI20032388A1 (en) * 2003-12-05 2005-06-06 Nuovo Pignone Spa VARIABLE NOZZLE FOR A GAS TURBINE.
DE102005040574A1 (en) * 2005-08-26 2007-03-15 Rolls-Royce Deutschland Ltd & Co Kg Gap control device for a gas turbine
DE102007021448B4 (en) * 2006-05-18 2012-06-28 Man Diesel & Turbo Se Diaphragm for an exhaust gas turbocharger operated with heavy oil reciprocating internal combustion engine
US8534990B2 (en) * 2009-11-11 2013-09-17 Hamilton Sundstrand Corporation Inlet guide vane drive system with spring preload on mechanical linkage

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB755527A (en) * 1953-10-15 1956-08-22 Power Jets Res & Dev Ltd Mounting of swivelling guide vane elements in axial flow elastic fluid turbines
CH360074A (en) * 1957-10-31 1962-02-15 Maschf Augsburg Nuernberg Ag Diffuser with adjustable blades during operation, especially for gas turbines
US3013771A (en) * 1960-10-18 1961-12-19 Chrysler Corp Adjustable nozzles for gas turbine engine
GB1211447A (en) * 1968-09-17 1970-11-04 Leyland Gas Turbines Ltd Turbine having variable angle nozzle guide vanes

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2206381A (en) * 1987-06-30 1989-01-05 Rolls Royce Plc A variable stator vane arrangement for a compressor
US4812106A (en) * 1987-06-30 1989-03-14 Rolls-Royce Plc Variable stator vane arrangement for a compressor
GB2206381B (en) * 1987-06-30 1991-10-09 Rolls Royce Plc A variable stator vane arrangement for a compressor

Also Published As

Publication number Publication date
SE360425B (en) 1973-09-24
AT309913B (en) 1973-09-10
DE2039064B2 (en) 1972-07-06
ZA705605B (en) 1971-04-28
NL7012074A (en) 1971-02-16
CS149924B2 (en) 1973-08-23
DE2039064C3 (en) 1974-05-09
CH520267A (en) 1972-03-15
CA940051A (en) 1974-01-15
DE2039064A1 (en) 1971-09-02
FR2055780A1 (en) 1971-04-30
ES382608A1 (en) 1974-12-16
US3685921A (en) 1972-08-22

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Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
PCNP Patent ceased through non-payment of renewal fee