FR2321616A1 - Axial flow compressor stator blade fixing - uses U section seal around slot across carrier ring and fitting rectangular blade base - Google Patents

Axial flow compressor stator blade fixing - uses U section seal around slot across carrier ring and fitting rectangular blade base

Info

Publication number
FR2321616A1
FR2321616A1 FR7525843A FR7525843A FR2321616A1 FR 2321616 A1 FR2321616 A1 FR 2321616A1 FR 7525843 A FR7525843 A FR 7525843A FR 7525843 A FR7525843 A FR 7525843A FR 2321616 A1 FR2321616 A1 FR 2321616A1
Authority
FR
France
Prior art keywords
collar
flow compressor
axial flow
seal around
carrier ring
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.)
Granted
Application number
FR7525843A
Other languages
French (fr)
Other versions
FR2321616B1 (en
Inventor
Claude Dubois
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.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
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 SNECMA SAS filed Critical SNECMA SAS
Priority to FR7525843A priority Critical patent/FR2321616A1/en
Publication of FR2321616A1 publication Critical patent/FR2321616A1/en
Application granted granted Critical
Publication of FR2321616B1 publication Critical patent/FR2321616B1/fr
Granted legal-status Critical Current

Links

Classifications

    • 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
    • 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

Landscapes

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

Abstract

A double flow compressor for an aircraft jet engine has a ring of stator blades (2) mounted between an outside collar (3) and an inside collar (6). The top (8) of each blade flanges outwards, and is cross-shaped in end view, and is secured by a bolt (10) and nut (11) to the outside collar. The base (13) fits into the inside collar (6) with a flexible seal (15). This seal is of U-section and fits all round a diagonal slot across the inside collar. The base (13) of the blade is rectangular, with a rib (13a) extending downwards underneath. This arrangement permits blades to be easily interchanged after the upper securing bolts (10) have been removed. They are then angled out from the sound deadening panels (5) under the outside collar.
FR7525843A 1975-08-21 1975-08-21 Axial flow compressor stator blade fixing - uses U section seal around slot across carrier ring and fitting rectangular blade base Granted FR2321616A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR7525843A FR2321616A1 (en) 1975-08-21 1975-08-21 Axial flow compressor stator blade fixing - uses U section seal around slot across carrier ring and fitting rectangular blade base

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR7525843A FR2321616A1 (en) 1975-08-21 1975-08-21 Axial flow compressor stator blade fixing - uses U section seal around slot across carrier ring and fitting rectangular blade base

Publications (2)

Publication Number Publication Date
FR2321616A1 true FR2321616A1 (en) 1977-03-18
FR2321616B1 FR2321616B1 (en) 1979-06-15

Family

ID=9159235

Family Applications (1)

Application Number Title Priority Date Filing Date
FR7525843A Granted FR2321616A1 (en) 1975-08-21 1975-08-21 Axial flow compressor stator blade fixing - uses U section seal around slot across carrier ring and fitting rectangular blade base

Country Status (1)

Country Link
FR (1) FR2321616A1 (en)

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0219445A1 (en) * 1985-09-30 1987-04-22 United Technologies Corporation Compressor stator assembly having a composite inner diameter shroud
FR2599081A1 (en) * 1986-05-23 1987-11-27 Snecma Multiple-bypass turbine engine blower straightener
EP0250324A1 (en) * 1986-06-18 1987-12-23 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Guide vane for a fan turbine
EP0277884A2 (en) * 1987-02-05 1988-08-10 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Outer stator shroud of a fan jet engine fitted on the fan housing
FR2636378A1 (en) * 1988-09-14 1990-03-16 Snecma Bypass turbojet blower nozzle guide vane
FR2674909A1 (en) * 1991-04-03 1992-10-09 Snecma Turbomachine compressor stator with dismantleable vanes
WO1995017584A1 (en) * 1993-12-22 1995-06-29 Alliedsignal Inc. Insertable stator vane assembly
EP0953729A1 (en) * 1998-05-01 1999-11-03 Techspace aero Guide vanes for a turbomachine
US6884024B2 (en) * 2002-03-26 2005-04-26 Mtu Aero Engines Gmbh Arrangement for the fastening of struts serving as bearing carriers for the rotor of an aeronautical gas turbine to the casing structure of the aeronautical gas turbine
EP1801357A1 (en) 2005-12-22 2007-06-27 Techspace aero Bladed nozzle of a turbomachine, turbomachine comprising this nozzle and turbomachine vane
EP2025865A3 (en) * 2007-08-13 2012-08-01 United Technologies Corporation Fan outlet guide vane shroud insert repair
FR2980249A1 (en) * 2011-09-20 2013-03-22 Snecma Structural intermediate casing for e.g. turbojet of aircraft, has set of non-structural rectifiers arranged interdependent of hub, where non-structural rectifiers are fixed in removable manner by its ends internally at internal ring
FR3076571A1 (en) * 2018-01-10 2019-07-12 Safran Aircraft Engines RECTIFIER FOR TURBOMACHINE AND METHOD FOR DISASSEMBLING A BLADE OF THIS RECTIFIER
RU2709752C2 (en) * 2013-12-20 2019-12-19 Сафран Аэро Бустерс Са Sealing ring of internal ring of last stage of gas turbine engine axial compressor

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
NEANT *

Cited By (23)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0219445A1 (en) * 1985-09-30 1987-04-22 United Technologies Corporation Compressor stator assembly having a composite inner diameter shroud
FR2599081A1 (en) * 1986-05-23 1987-11-27 Snecma Multiple-bypass turbine engine blower straightener
EP0250324A1 (en) * 1986-06-18 1987-12-23 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Guide vane for a fan turbine
FR2600379A1 (en) * 1986-06-18 1987-12-24 Snecma MULTIFLUX TURBOJET BLOWER RECTIFIER
US4820120A (en) * 1986-06-18 1989-04-11 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Stator assembly for the fan of a multi-flow turbo-jet engine
EP0277884A2 (en) * 1987-02-05 1988-08-10 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Outer stator shroud of a fan jet engine fitted on the fan housing
FR2610673A1 (en) * 1987-02-05 1988-08-12 Snecma TURBOREACTOR MULTIFLUX WITH EXTERNAL CROWN OF BLOWER RECTIFIER FREQUENCY ON THE CARTER
US4940386A (en) * 1987-02-05 1990-07-10 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Multiple flow turbojet engine with an outer ring of the fan outlet shrunk onto the case
EP0277884A3 (en) * 1987-02-05 1990-07-11 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Outer stator shroud of a fan jet engine fitted on the fan housing
FR2636378A1 (en) * 1988-09-14 1990-03-16 Snecma Bypass turbojet blower nozzle guide vane
FR2674909A1 (en) * 1991-04-03 1992-10-09 Snecma Turbomachine compressor stator with dismantleable vanes
WO1995017584A1 (en) * 1993-12-22 1995-06-29 Alliedsignal Inc. Insertable stator vane assembly
US5494404A (en) * 1993-12-22 1996-02-27 Alliedsignal Inc. Insertable stator vane assembly
EP0953729A1 (en) * 1998-05-01 1999-11-03 Techspace aero Guide vanes for a turbomachine
US6296442B1 (en) * 1998-05-01 2001-10-02 Techspace Aero Turbomachine stator vane set
WO2004074639A1 (en) * 1998-05-01 2004-09-02 Hung Quac Tran Turbomachine guide bucket
US6884024B2 (en) * 2002-03-26 2005-04-26 Mtu Aero Engines Gmbh Arrangement for the fastening of struts serving as bearing carriers for the rotor of an aeronautical gas turbine to the casing structure of the aeronautical gas turbine
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
EP2025865A3 (en) * 2007-08-13 2012-08-01 United Technologies Corporation Fan outlet guide vane shroud insert repair
FR2980249A1 (en) * 2011-09-20 2013-03-22 Snecma Structural intermediate casing for e.g. turbojet of aircraft, has set of non-structural rectifiers arranged interdependent of hub, where non-structural rectifiers are fixed in removable manner by its ends internally at internal ring
RU2709752C2 (en) * 2013-12-20 2019-12-19 Сафран Аэро Бустерс Са Sealing ring of internal ring of last stage of gas turbine engine axial compressor
FR3076571A1 (en) * 2018-01-10 2019-07-12 Safran Aircraft Engines RECTIFIER FOR TURBOMACHINE AND METHOD FOR DISASSEMBLING A BLADE OF THIS RECTIFIER

Also Published As

Publication number Publication date
FR2321616B1 (en) 1979-06-15

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Legal Events

Date Code Title Description
ST Notification of lapse