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GB1238405A - - Google Patents

Info

Publication number
GB1238405A
GB1238405A GB2815169A GB1238405DA GB1238405A GB 1238405 A GB1238405 A GB 1238405A GB 2815169 A GB2815169 A GB 2815169A GB 1238405D A GB1238405D A GB 1238405DA GB 1238405 A GB1238405 A GB 1238405A
Authority
GB
United Kingdom
Prior art keywords
compressor
turbine
struts
rotor
diffuser
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
GB2815169A
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 filed Critical
Publication of GB1238405A publication Critical patent/GB1238405A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
    • F02C3/145—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant the combustion chamber being in the reverse flow-type
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/243—Flange connections; Bolting arrangements
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/26—Double casings; Measures against temperature strain in casings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation

Landscapes

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

Abstract

1,238,405. Gas turbine engines. K. I. ZHDANOV; A. G. TOMILIN; A. M. POLYAKOV; A. A. LUZHIN; S. G. P. KAINOV; J. N. VASILIEV; N. A. SHEREMET; J. G. BEKHLI and E. P. FEDOROV. June 4, 1969. No. 28151/69. Heading F1G. A gas turbine plant comprises a compressor, combustion equipment a turbine having a rotor connected to a rotor of the compressor, a diffuser located between the compressor and the turbine, the stator of the turbine being supported by the diffuser and thereby connected to the stator of the compressor, there being means for compensating for temperature deformation between the diffuser and the turbine stator. The engine shown comprises a compressor 1, combustion equipment 4 and turbine 3 connected to drive the compressor through shaft 14 also an external load through shaft 16. The compressor comprises a rotor 7 and a stator casing 9, the rotor having a combined axial and radial flow stage 6 and two axial flow stages 7. Air from the compressor passes through diffuser 2 to the combustion section which is of the reverse-flow type and comprises inner and outer walls 13, 27 with an annular flame tube 28 disposed therebetween, the wall 13 being the turbine stator casing. Gases pass from the flame tube through duct 37 and are directed by inlet guide vanes 17 on to the blades of turbine rotor 12, the gases finally discharging through outlet 38. The diffuser 2 is secured to the stator casing 9 of the compressor and is formed integrally with struts 11 which extend axially and are secured to the turbine stator casing 13 by the device 5 which permits differential expansion. The inlet end of the stator casing 13 is formed with a radial flange 18 in which are formed slots 19. Bolt members 22 are secured to the ends of the struts 11, see Fig. 3, each bolt carrying a slider 20 which is received in a radial slot 19, a pair of washers 24 having co-operating part-spherical surfaces 25a, 25b being retained against the slider by the head 23 of the bolt. Hollow struts 31 extends across the gas duct 37 and the struts 11 extend through the struts 31 with an annular passage 35 therebetween through which air flows to the inner air space of the combustion equipment.
GB2815169A 1969-06-04 1969-06-04 Expired GB1238405A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB2815169 1969-06-04

Publications (1)

Publication Number Publication Date
GB1238405A true GB1238405A (en) 1971-07-07

Family

ID=10271099

Family Applications (1)

Application Number Title Priority Date Filing Date
GB2815169A Expired GB1238405A (en) 1969-06-04 1969-06-04

Country Status (2)

Country Link
FR (1) FR2049325A5 (en)
GB (1) GB1238405A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3709637A (en) * 1970-08-14 1973-01-09 Secr Defence Gas turbine engines
WO1991007572A1 (en) * 1989-11-20 1991-05-30 Allied-Signal Inc. High temperature turbine engine structure
US5228284A (en) * 1988-12-06 1993-07-20 Allied-Signal Inc. High temperature turbine engine structure
US5279031A (en) * 1988-12-06 1994-01-18 Alliedsignal Inc. High temperature turbine engine structure

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3709637A (en) * 1970-08-14 1973-01-09 Secr Defence Gas turbine engines
US5116158A (en) * 1988-12-06 1992-05-26 Allied-Signal Inc. High temperature turbine engine structure
US5228284A (en) * 1988-12-06 1993-07-20 Allied-Signal Inc. High temperature turbine engine structure
US5279031A (en) * 1988-12-06 1994-01-18 Alliedsignal Inc. High temperature turbine engine structure
WO1991007572A1 (en) * 1989-11-20 1991-05-30 Allied-Signal Inc. High temperature turbine engine structure

Also Published As

Publication number Publication date
FR2049325A5 (en) 1971-03-26

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Legal Events

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