GB960812A - Compressor for a gas turbine engine - Google Patents

Compressor for a gas turbine engine

Info

Publication number
GB960812A
GB960812A GB1399763A GB1399763A GB960812A GB 960812 A GB960812 A GB 960812A GB 1399763 A GB1399763 A GB 1399763A GB 1399763 A GB1399763 A GB 1399763A GB 960812 A GB960812 A GB 960812A
Authority
GB
United Kingdom
Prior art keywords
compressor
rings
ring
slots
stator
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
GB1399763A
Inventor
Norman Robert Robinson
Wallace Alfred Winfield
Douglas Herbert Williamson
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 GB1399763A priority Critical patent/GB960812A/en
Priority to DE19641428223 priority patent/DE1428223A1/en
Priority to FR969734A priority patent/FR1389254A/en
Publication of GB960812A publication Critical patent/GB960812A/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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • F01D9/044—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators permanently, e.g. by welding, brazing, casting or the like
    • 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
    • F01D25/246—Fastening of diaphragms or stator-rings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

960,812. Axial-flow compressors; jet propulsion plant; compressor blade mounting. ROLLSROYCE Ltd. April 8, 1963, No. 13997/63. Headings F1C, F1J and FIT. A compressor 13, Figs. 1 and 2, for a gas turbine engine comprises a cylindrical outer casing 20 within which is secured an inner casing 21 which has a series of axially consecutive rings 23-30 each provided with at least one stage of stator blades 33, the series of rings comprising a number of axially consecutive unsplit rings 23-26 disposed at the upstream portion of the compressor and at least one ring 27-30 split substantially axially and arranged at the downstream portion of the compressor, the or each split ring 27-30 being provided with support means directly connected to the outer casing 20. The rings 27-30, having strengthening ribs 9, are split along a sinuous line 48, Fig. 3 (not shown), extending substantially axially between the stator blades 33. These rings are supported from the outer casing 20 by flanges 36 having rims 37 located in slots 38. Each flange 36 is provided with a number of slots 40 and holes 41, Fig. 4, to increase its resilience so that the rings 27-30 may conform to the shape of the casing 20 during cold start and hot shutdown conditions. The resilience of each of the adjacent flanges 36a is increased by cut outs (shown in dash lines) which are so arranged that each flange 36a closes the slots 40 of the associated flange 36 and thereby prevents recirculation of air between chambers 22a, 22b, 22c and 22d, which may be vented to the compressor 13 by small holes (not shown) for pressure balancing purposes. Air may be bled from the compressor 13 into a by-pass passage 16 of the engine through openings between the blades of the upstream stator stage of ring 28, the chamber 22b and a control valve 45. The upstream stator stage of ring 28 is made by welding or brazing together adjacent blade platforms. The remainder of the stator stages are formed by welding or brazing substantially elliptical platforms into correspondingly shaped slots in the respective ring 23-30, the radial thicknesses of the ring and platforms being substantially the same.
GB1399763A 1963-04-08 1963-04-08 Compressor for a gas turbine engine Expired GB960812A (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
GB1399763A GB960812A (en) 1963-04-08 1963-04-08 Compressor for a gas turbine engine
DE19641428223 DE1428223A1 (en) 1963-04-08 1964-04-01 Compressor for gas turbine jet engine
FR969734A FR1389254A (en) 1963-04-08 1964-04-03 Compressor for gas turbine engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1399763A GB960812A (en) 1963-04-08 1963-04-08 Compressor for a gas turbine engine

Publications (1)

Publication Number Publication Date
GB960812A true GB960812A (en) 1964-06-17

Family

ID=10033142

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1399763A Expired GB960812A (en) 1963-04-08 1963-04-08 Compressor for a gas turbine engine

Country Status (2)

Country Link
DE (1) DE1428223A1 (en)
GB (1) GB960812A (en)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2139292A (en) * 1983-05-02 1984-11-07 Mtu Muenchen Gmbh Compressor casings
US4875828A (en) * 1985-03-14 1989-10-24 Mtu Motoren-Und Turbinen-Union Munchen Gmbh Turbo-engine having means for controlling the radial gap
EP1801357A1 (en) 2005-12-22 2007-06-27 Techspace aero Bladed nozzle of a turbomachine, turbomachine comprising this nozzle and turbomachine vane
EP1936125A1 (en) 2006-12-22 2008-06-25 Techspace Aero Turbomachine compressor
GB2445952A (en) * 2007-01-25 2008-07-30 Siemens Ag Stator for compressing a fluid
CN111594275A (en) * 2019-02-20 2020-08-28 通用电气公司 Turbomachine having an airflow management assembly
EP4234889A1 (en) * 2022-02-25 2023-08-30 Rolls-Royce plc Casing assembly for gas turbine engine

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102016204660A1 (en) * 2016-03-22 2017-09-28 MTU Aero Engines AG Method for producing a housing of a turbomachine and housing of a turbomachine

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2139292A (en) * 1983-05-02 1984-11-07 Mtu Muenchen Gmbh Compressor casings
US4875828A (en) * 1985-03-14 1989-10-24 Mtu Motoren-Und Turbinen-Union Munchen Gmbh Turbo-engine having means for controlling the radial gap
EP1801357A1 (en) 2005-12-22 2007-06-27 Techspace aero Bladed nozzle of a turbomachine, turbomachine comprising this nozzle and turbomachine vane
US7722321B2 (en) 2005-12-22 2010-05-25 Techspace Aero Turbo-engine stator blading, turbo-engine comprising the blading and turbo-engine blade
EP1936125A1 (en) 2006-12-22 2008-06-25 Techspace Aero Turbomachine compressor
GB2445952A (en) * 2007-01-25 2008-07-30 Siemens Ag Stator for compressing a fluid
GB2445952B (en) * 2007-01-25 2011-07-20 Siemens Ag A gas turbine engine
US8714922B2 (en) 2007-01-25 2014-05-06 Siemens Aktiengesellschaft Diffuser for decelerating a compressed fluid
CN111594275A (en) * 2019-02-20 2020-08-28 通用电气公司 Turbomachine having an airflow management assembly
EP4234889A1 (en) * 2022-02-25 2023-08-30 Rolls-Royce plc Casing assembly for gas turbine engine
US11753966B1 (en) 2022-02-25 2023-09-12 Rolls-Royce Plc Casing assembly for gas turbine engine

Also Published As

Publication number Publication date
DE1428223A1 (en) 1969-07-10

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