EP0174892A1 - Abblasventil für einen Kompressor - Google Patents

Abblasventil für einen Kompressor Download PDF

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Publication number
EP0174892A1
EP0174892A1 EP85401706A EP85401706A EP0174892A1 EP 0174892 A1 EP0174892 A1 EP 0174892A1 EP 85401706 A EP85401706 A EP 85401706A EP 85401706 A EP85401706 A EP 85401706A EP 0174892 A1 EP0174892 A1 EP 0174892A1
Authority
EP
European Patent Office
Prior art keywords
ring
plates
compressor
casing
elastically deformable
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
EP85401706A
Other languages
English (en)
French (fr)
Other versions
EP0174892B1 (de
Inventor
Jean Georges Bouiller
Gérard Ernest André Jourdain
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
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
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 Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0174892A1 publication Critical patent/EP0174892A1/de
Application granted granted Critical
Publication of EP0174892B1 publication Critical patent/EP0174892B1/de
Expired legal-status Critical Current

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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
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
    • F04D27/0215—Arrangements therefor, e.g. bleed or by-pass valves
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
    • F04D27/023—Details or means for fluid extraction

Definitions

  • the invention relates to a compressor discharge device; it relates in particular to the means for supporting and guiding a ring forming a valve controlling a compressor discharge opening.
  • the usual discharge means comprise several pivoting hatches distributed around the periphery of the casing and controlled in synchronism. These hatches must offer a large passage section, be able to open and close quickly, and have a good seal in the closed position so as not to affect the performance of the engine. To fulfill these conditions, we are led to produce heavy, complicated devices and of considerable size. In addition, the opening of these hatches creates in the veins of the wakes, heterogeneities likely to disturb the operation of the downstream compressor.
  • Such a ring being of large diameter, is actuated by a plurality of jacks distributed around its periphery. Usually, it is supported and guided in its movement by means of shoes, rollers cooperating with sliding or rolling surfaces such as rails or slides.
  • Patent DE 2,060,509 also shows guide means where rails integral with the ring cooperate with rollers mounted on the casing.
  • the invention aims to remedy these drawbacks and proposes to support the ring by means of one or more elastically deformable body consisting of at least one plate of elastomeric material or equivalent comprised between two rigid plates to which it is linked by bonding, vulcanization or any other means. These two plates are themselves integral one of the ring, the other of the housing and arranged parallel to the direction of movement.
  • this body consists of an alternating stack of elastomeric plates and rigid plates adhering to each other and parallel to the first two.
  • the centering of the ring can be obtained by the combination of at least three peripherally distributed bodies whose plates are arranged radially.
  • the blocks are preloaded for assembly, they ensure that the ring is locked in the closed position even if the actuation mechanism is released.
  • Figure I is therefore an axial sectional view of part of the intermediate pressure compressor of a turbofan engine with high dilution rate.
  • the air from the low pressure compressor is divided into a primary flow and a secondary flow.
  • the primary flow is compressed by the intermediate pressure compressor and the high pressure compressor arranged in series, then it passes through the combustion chamber and the successive stages of turbines before being ejected into the atmosphere.
  • the secondary flow is ejected directly into the atmosphere and provides most of the thrust.
  • the medium pressure compressor 3 the end of a movable fin 3 ′ of the top stage of which can be seen, and the end of a distributor fin 3 "is mechanically independent of the high pressure compressor (not shown) located downstream.
  • This valve is constituted by a ring 10 cooperating with an annular slot 4 formed in the external wall 5 of the vein 1.
  • This slot has edges 41 and 42 parallel and perpendicular to the axis of the engine. In the embodiment shown it occupies a frusto-conical band between the fins 3 'and 3 ".
  • the ring 10 is axially movable in a space delimited on the one hand, by the wall 5 and the internal wall 7 of the vein 2, on the other hand, upstream, by a conical ferrule 53 connecting the wall 5, at the edge 41, to a radial flange 71 of the wall 7 and, downstream by a radial flange 72 connecting the walls 5 and 7.
  • An internal ferrule 74 cylindrical connects the radial flanges 71 and 72; it includes cutouts, as shown in FIG. I for the passage of deflected air which passes through the wall 7 by exhaust grids 75 made up of sectors assembled peripherally in an annular cutout of the casing forming the wall 7. These sectors have vanes arranged in parallel rows and inclined so that the discharged air disturbs the flow in the secondary vein as little as possible.
  • the ring 10 is in the form of a gutter oriented along the axis of the engine. It consists of two skins 11 and 12 made of sheet metal or preferably of composite material, curved section, encased in one another so as to provide a cavity 13 therebetween. This cavity is filled with a filling material ensuring the stiffening of the ring, for example a resin loaded with hollow glass beads.
  • the outer skin 11 has an inner wing 111 of cylindrical shape, the diameter of which corresponds to that of the outer surface formed on the wall 5 at the edge 42.
  • This cylindrical wing 111 is extended by a frustoconical portion 112 whose geometry corresponds to the wall portion 5 missing through the slot 4 made in this wall; at its largest diameter is connected a second frusto-conical portion 113 terminated by a second cylindrical wing 114 concentric with the first and of larger diameter.
  • the second skin 12 also includes two wings 121 and 123 secured by any appropriate means, rivet, bonding, etc., to the wings 111 and 114.
  • the annular cavity 13 is thus delimited by the skin 11 and the part 122 of the skin 12 connecting the wings 121 and 123.
  • This ring 10 is movable in translation inside the ferrule 74 between a first position where the part 112 closes the slot 4 and a recessed position releasing the latter. In this first position, the sealing of the vein 1 is ensured by two beads.
  • a bead 15 mounted on the inner face of the ring bears on a radial flange 51 of the wall 5.
  • a bead 52 housed in the angle formed by the ferrule 53 and the wall 5 serves as a support at the front end of the ring. This is driven by several axial cylinders 6, with screws, synchronized, distributed regularly around the periphery. There are at least three cylinders, preferably six.
  • each jack is subject to the radial flange 72, the latter has openings allowing the passage of two jack rods 62, one end of which mite is fixed to a guide 63 sliding in a lateral slide of the body 61 and the other end is connected to the ring 10.
  • the ring 10 is supported in the casing by means of elastically deformable bodies 8, also providing guidance during its movement from the open position to the closed position.
  • Each body consists of two blocks 81, 82 formed by alternating layers parallel to the axis of the ring of plates of elastomeric material 83 and rigid plates 84, metallic for example, vulcanized together or linked by any other means.
  • These laminated blocks are of rectangular shape and are assembled by their metal end plate 85 so as to constitute a V-shaped body whose opening is directed upstream.
  • the plates 85 of the top of the body are fixed by a pin 86 to a yoke 66 integral with the body of the jack 61.
  • Each end of the branches of the V comprises two metal plates 87, welded together, the downstream end of which flares out to form a yoke 88 which agrees with that of the end of the arms 62, of the jack 6.
  • These plates 87 also include lugs by which they are fixed by gluing or riveting or any other means to the wings of the ring.
  • the operation of the device is as follows.
  • the six jacks are actuated simultaneously.
  • the rods of the cylinders move downstream causing the sliding of the ring and the opening of the annular slot through which the compressor discharges.
  • the ring is guided by laminated blocks which gradually deform; referring to the lower half of Figure 2 we see the two extreme shapes taken by these blocks.
  • the V-shaped arrangement allows them to work essentially in compression while allowing a significant stroke of the ring. This stroke corresponds to the symmetrical reversal of the branches of the V as shown in Figure 2.
  • these blocks are prestressed so that already in closing function, the ring is subjected to a pressing force against the seals. This avoids vibrations and any untimely opening in the event of the cylinders being released. In the event of failure of the control while the ring is in the open position, the restoring force is sufficient to cause the ring to close by itself.

Landscapes

  • Engineering & Computer Science (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP85401706A 1984-09-06 1985-09-03 Abblasventil für einen Kompressor Expired EP0174892B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8413694A FR2569785B1 (fr) 1984-09-06 1984-09-06 Disposit
FR8413694 1984-09-06

Publications (2)

Publication Number Publication Date
EP0174892A1 true EP0174892A1 (de) 1986-03-19
EP0174892B1 EP0174892B1 (de) 1988-03-09

Family

ID=9307480

Family Applications (1)

Application Number Title Priority Date Filing Date
EP85401706A Expired EP0174892B1 (de) 1984-09-06 1985-09-03 Abblasventil für einen Kompressor

Country Status (4)

Country Link
US (1) US4679982A (de)
EP (1) EP0174892B1 (de)
DE (1) DE3561835D1 (de)
FR (1) FR2569785B1 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3059367A1 (fr) * 2016-11-25 2018-06-01 Safran Aircraft Engines Turbomachine a double flux equipee d'un systeme de decharge

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5505587A (en) * 1995-01-05 1996-04-09 Northrop Grumman Corporation RAM air turbine generating apparatus
DE19834530A1 (de) * 1998-07-31 2000-02-03 Bmw Rolls Royce Gmbh Anordnung eines als Abblaseventil eines Axialverdichters fungierenden Blendenringes
GB2385382B (en) * 2002-02-13 2006-02-15 Rolls Royce Plc A cowl structure for a gas turbine engine
GB0618072D0 (en) * 2006-09-14 2006-10-25 Rolls Royce Plc Aeroengine nozzle
US8240126B2 (en) * 2008-03-22 2012-08-14 Pratt & Whitney Rocketdyne, Inc. Valve system for a gas turbine engine
US8402744B2 (en) * 2008-03-22 2013-03-26 Pratt & Whitney Rocketdyne, Inc. Valve system for a gas turbine engine
US8286416B2 (en) * 2008-04-02 2012-10-16 Pratt & Whitney Rocketdyne, Inc. Valve system for a gas turbine engine
US8578716B2 (en) * 2008-03-22 2013-11-12 United Technologies Corporation Valve system for a gas turbine engine
ES2343879B1 (es) * 2008-11-28 2011-08-02 Airbus Operations, S.L. Perfil de sellado y uso del mismo.
DE102011101331A1 (de) * 2011-05-12 2012-11-15 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinentriebwerk mit Zapfluftentnahmevorrichtung
US10393128B2 (en) 2015-05-26 2019-08-27 Pratt & Whitney Canada Corp. Translating gaspath bleed valve
FR3095005B1 (fr) * 2019-04-09 2021-03-19 Safran Aircraft Engines Turbomachine pour un aeronef

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3057541A (en) * 1958-06-03 1962-10-09 United Aircraft Corp Circumferential bleed valve
GB911535A (en) * 1959-08-24 1962-11-28 Rolls Royce Compressors for gas turbine engines
FR2068282A5 (de) * 1969-09-30 1971-08-20 Gen Electric
GB1357016A (en) * 1971-11-04 1974-06-19 Rolls Royce Compressor bleed valves
US4005612A (en) * 1975-10-31 1977-02-01 United Technologies Corporation Preloaded anti-rattle device
FR2349740A1 (fr) * 1976-04-26 1977-11-25 Boeing Co Berceau de turboreacteur a double flux a portes de contournement de stators
FR2359973A1 (fr) * 1976-07-27 1978-02-24 Kloeckner Humboldt Deutz Ag Moteur a explosion muni d'un turbocompresseur de suralimentation a gaz d'echappement
FR2402772A1 (fr) * 1977-09-10 1979-04-06 Mtu Muenchen Gmbh Dispositif pour actionner des organes d'arret dans des moteurs a turbine a gaz, notamment dans des moteurs a reaction
EP0029773A1 (de) * 1979-11-23 1981-06-03 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Schwenkbare Schubdüse für Strahlantrieb

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH469928A (fr) * 1968-01-19 1969-03-15 Lucifer Sa Valve comprenant au moins un clapet monté flottant
US3638428A (en) * 1970-05-04 1972-02-01 Gen Electric Bypass valve mechanism
DE2060509A1 (de) * 1970-12-09 1972-08-24 Motoren Turbinen Union Vorrichtung zum Abblasen von Verdichterluft

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3057541A (en) * 1958-06-03 1962-10-09 United Aircraft Corp Circumferential bleed valve
GB911535A (en) * 1959-08-24 1962-11-28 Rolls Royce Compressors for gas turbine engines
FR2068282A5 (de) * 1969-09-30 1971-08-20 Gen Electric
GB1357016A (en) * 1971-11-04 1974-06-19 Rolls Royce Compressor bleed valves
US4005612A (en) * 1975-10-31 1977-02-01 United Technologies Corporation Preloaded anti-rattle device
FR2349740A1 (fr) * 1976-04-26 1977-11-25 Boeing Co Berceau de turboreacteur a double flux a portes de contournement de stators
FR2359973A1 (fr) * 1976-07-27 1978-02-24 Kloeckner Humboldt Deutz Ag Moteur a explosion muni d'un turbocompresseur de suralimentation a gaz d'echappement
FR2402772A1 (fr) * 1977-09-10 1979-04-06 Mtu Muenchen Gmbh Dispositif pour actionner des organes d'arret dans des moteurs a turbine a gaz, notamment dans des moteurs a reaction
EP0029773A1 (de) * 1979-11-23 1981-06-03 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Schwenkbare Schubdüse für Strahlantrieb

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3059367A1 (fr) * 2016-11-25 2018-06-01 Safran Aircraft Engines Turbomachine a double flux equipee d'un systeme de decharge

Also Published As

Publication number Publication date
EP0174892B1 (de) 1988-03-09
DE3561835D1 (en) 1988-04-14
FR2569785A1 (fr) 1986-03-07
FR2569785B1 (fr) 1986-09-12
US4679982A (en) 1987-07-14

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