EP2071192A1 - Vorrichtung zum Luftabzug in einem Kompressor eines Turbotriebwerks - Google Patents

Vorrichtung zum Luftabzug in einem Kompressor eines Turbotriebwerks Download PDF

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Publication number
EP2071192A1
EP2071192A1 EP08168909A EP08168909A EP2071192A1 EP 2071192 A1 EP2071192 A1 EP 2071192A1 EP 08168909 A EP08168909 A EP 08168909A EP 08168909 A EP08168909 A EP 08168909A EP 2071192 A1 EP2071192 A1 EP 2071192A1
Authority
EP
European Patent Office
Prior art keywords
compressor
sheet
air
screen
flange
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
EP08168909A
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English (en)
French (fr)
Other versions
EP2071192B1 (de
Inventor
Antoine Robert Alain Brunet
Laurent Jablonsky
Sébastien Juste
Julien Sedlak
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
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Publication date
Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of EP2071192A1 publication Critical patent/EP2071192A1/de
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Publication of EP2071192B1 publication Critical patent/EP2071192B1/de
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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
    • 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
    • F04D29/545—Ducts
    • 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

Definitions

  • the invention relates to a turbomachine compressor equipped with an air sampling system and to a turbomachine such as a turbojet engine or an airplane turboprop engine equipped with a compressor of this type.
  • a turbomachine with a double flow comprises an upstream air inlet which is divided into a primary air flow supplying compression and combustion stages, and a secondary air flow bypassing the turbojet engine and joining the turbojet engine outlet. the primary air flow.
  • a portion of the air passing through the compressor is taken for various uses, including pressurizing the cabin, defrosting or ventilating the turbine of the turbojet engine to cool it.
  • Air sampling is generally carried out in the high-pressure compressor which comprises an outer casing for stiffening the compression stage and a wall delimiting externally the flow vein of the primary air flow inside the high-pressure compressor. and formed by an arrangement of annular segments, some bearing rectifiers and the others, alternately arranged with the previous ones, extend to the radially outer end of the moving wheels.
  • the outer casing comprises an orifice on which is mounted a suction duct and which opens into an annular space formed between an annular segment of a rectifier stage and an annular segment of a mobile wheel.
  • part of the air circulating in the primary air stream of the high-pressure compressor is taken from the inter-segment space and conveyed to equipment requiring pressurized air by means of the suction duct opening in the outer casing.
  • the functioning engine In certain critical situations, such as an engine failure, the functioning engine must be able to withstand all air sampling. For example, in normal operation, the maximum sampling is about 8% of the average compressor flow and in case of failure of one engine, the other engine must be able to provide up to 16% of its average flow, which can 'prove impossible in the case of strong heterogeneities of static pressure around the axis of the compressor.
  • the invention particularly aims to limit the static pressure variations around the axis of the turbomachine while maintaining the same air bleed capacity in the high pressure compressor.
  • a turbomachine compressor such as a high-pressure compressor, comprising air sampling means comprising a duct whose suction end opens into an outer casing of the compressor at a mobile wheel and a rectifier stage of the compressor, characterized in that a ring-shaped screen plate is mounted radially inside the housing opposite a portion of the suction end of the duct so as to standardize 360 ° air sampling around the compressor axis.
  • the screen sheet comprises at its upstream end radial support means on a housing flange, the downstream end of the sheet being fixed by screws on an annular flange of the rectifier stage. mounted downstream of the moving wheel.
  • the screen sheet is thus mounted on pre-existing mechanical parts, and its integration into the environment of the high-pressure compressor does not require any structural modification thereof.
  • the support means of the screen sheet comprise cylindrical rims extending upstream.
  • the screen sheet preferably extends over less than 360 ° and has a cylindrical flange at each of its circumferential ends. It can thus be supported on the flange of the housing only at its circumferential ends and the air flow can flow between the flange and the upstream end of the sheet.
  • the limitation of the circumferential extent of the sheet makes it possible to maintain a mean static pressure around the axis of the compressor which is similar to that of the prior art, which avoids resorting to other sources of sampling. air that would increase fuel consumption.
  • the screen sheet extends over approximately 234 ° and its end cylindrical rims extend angularly over several tens of degrees.
  • the downstream end of the screen sheet may comprise large diameter holes alternately arranged with small diameter holes provided for the passage of fixing screws.
  • the screen plate is fixed to the annular flange of the floor downstream rectifier only by screws inserted into the small diameter holes and tightened on the flange.
  • Large diameter holes are used only for the passage of screw heads securing the flange of the downstream rectifier with a flange of the next downstream rectifier stage.
  • the screen sheet does not participate in the mechanical strength of the compressor stage, it is not necessary to fix it to the flange of the downstream rectifier stage with a large number of fixing screws.
  • Support of the upstream end of the screen plate can be performed with an elastic preload bearing on the flange of the housing.
  • the rectifier stage located upstream of the mobile wheel is fixed to the flange of the housing by a shell comprising air passage holes, of which those located at a central portion of the screen plate are completely closed while those located opposite the end portions of the screen plate are 50% closed.
  • the total or partial closure of the holes of the shell makes it possible to better control the distribution of the air sample around the axis of the turbomachine.
  • the screen sheet also comprises at least one orifice of passage of an endoscope for checking the state of compressor parts located radially inside the screen sheet.
  • the invention also proposes a ring-shaped screen sheet intended to be used in a compressor of the type described above, characterized in that its section is of L-shaped and in that it comprises a cylindrical wall connected to one end. a radial wall having fixing screw holes, the other end being connected to a frustoconical wall.
  • the frustoconical wall of the screen sheet has radial flanges oriented outwardly at its circumferential ends.
  • the invention also relates to a turbomachine, such as a turbojet or an airplane turboprop, characterized in that it comprises a compressor of the type described above.
  • FIG 1 represents a downstream part of a high-pressure compressor 10 of axis 12, mounted downstream of a low-pressure compressor and upstream of a combustion chamber.
  • the high-pressure compressor 10 comprises an outer casing 14 and a wall 16 in which a plurality of movable wheels 18, 20, 22 are rotated alternately with rectifying stages 24, 26, 28.
  • the wall 16 comprises a series of annular segments of which the ones 30, 32, 34 carry the radially outer ends of the rectifiers 24, 26, 28 and the others 36, 38, 40, arranged alternately with the previous ones, are opposite the radially outer ends of the mobile wheels 18, 20, 22
  • the annular segments are interconnected by means of annular flanges 42, 44, 46, 48 and are connected together to the outer casing 14.
  • An air sampling is provided between a rectifier stage 24 and a downstream movable wheel 18 by axially spacing the downstream end of the segment 30 of the upstream rectifier stage 24 and the upstream end of the segment 36 disposed opposite the movable wheel 18.
  • the segment 30 of the upstream rectifier stage 24 is connected to the outer casing 14 by a ferrule 52 extending downstream and fixed at its radially outer end to an inner flange 54 of the housing 14.
  • the ferrule 52 comprises a plurality of air passage holes 56 distributed on its circumference.
  • the means for withdrawing air from the compressor 10 comprise a duct 58 whose suction end is mounted on an orifice 60 of the outer casing 14. This orifice 60 is positioned axially on the outer casing 14 so that it is located opposite the inter-segment space 61. Its diameter is such that it opens on either side of the ferrule 52 for fixing the upstream rectifier stage 24.
  • the flow of air entering the turbomachine is divided into two parts, one of which corresponds to a primary air flow through the high-pressure compressor 10.
  • This graph shows that most of the air sampling is done in the immediate vicinity and right of the suction hole 60, which leads to significant static pressure variations around the axis 12 of the high-pressure compressor 10.
  • the invention overcomes this problem as well as those mentioned above by mounting a sheet 62 of annular shape inside the outer casing 14, to form a screen facing a portion of the suction end of the duct 58 so as to standardize the air sampling over 360 ° around the axis 12 of the high-pressure compressor 10 ( figure 3 and 4 ).
  • the screen sheet 62 extends over less than 360 ° and has an axial section of L-shape. It comprises a cylindrical wall 64 connected at its downstream end to a radial wall 66, its upstream end being connected to a frustoconical wall 68 to section increasing upstream.
  • the upstream end of the frustoconical wall 68 comprises radial support means on the flange 54 for fixing the ferrule 52 of the upstream rectifier stage 24 ( figure 3 and 5 ).
  • These means include ledges 70 of cylindrical shape extending upstream.
  • the flanges 70 are formed at each of the circumferential ends of the sheet 62 and extend angularly over several tens of degrees.
  • the radial wall 66 is fixed to annular flanges 42, 44 for fixing the annular segments 36, 38. It comprises small diameter holes 72 alternating with holes of larger diameter 74.
  • the small diameter holes 72 allow the passage of fastening screw and the tightening of the screw heads on the radial wall 66.
  • the large diameter holes 74 have a sufficiently large diameter to allow the passage of the heads of these same screws. These holes 74 are not used for clamping the radial wall 66.
  • the holes 56 of the ferrule 52 for fixing the upstream rectifier stage 24 which are situated at the central part of the screen plate 62 are completely closed while the holes 56 situated opposite the end portions 70 of the sheet metal screen 66 are 50% closed.
  • the air taken from the compressor 10 flows between the radially inner end of the flange 54 for fixing the upstream rectifier stage 24 and the upstream end of the frustoconical wall 68 of the screen plate. 62 (arrow F1).
  • the reduced spacing between the flange 54 and the upstream end of the sheet 62 as well as the total closure of the holes 56 of the upstream shell 52 in the central portion of the sheet 62 limits the air intake to the right of the led 58, which avoids a drop in the static pressure in this place (curve B of the figure 2 ).
  • the arrow F2 indicates the flow of air coming from the compressor 10 and passing through the unsealed or partially closed holes 56 of the ferrule 52 of the upstream rectifier stage 24 which are located near the circumferential ends 70 of the plate 62.
  • the air taken in the high pressure compressor 10 flows between the sheet 62 and the outer casing 14 and then sucked into the conduit 58 (arrows F3).
  • this sheet does not reduce the air sampling capacity of the duct since the average static pressures with and without screen plate 62 are substantially similar and of the order of 2.75 u.a.
  • the screen plate 62 may be mounted at its upstream end with an elastic preload bearing on the flange of the outer casing, which ensures a permanent contact of the sheet on the flange. In operation, the air sucked into the duct 58 makes it possible to further press the upstream end of the sheet on the flange 54 of the casing 14.
  • a compressor casing usually comprises one or more orifices allowing the passage of an endoscope 75 for exploration of the inside of the compressor.
  • the sheet 62 may comprise at least one orifice 76 allowing the passage of such an endoscope.
  • the screen sheet extends over at least 180 ° and at most about 270 °.
  • the screen sheet extends over 234 ° and comprises a cylindrical flange 70 extending between 0 ° and 36 °, the other flange extending between 180 ° and 234 °.
  • the axial dimension of the sheet is 36.3 mm at its circumferential ends and 30 mm outside.
  • the thickness of the sheet is of the order of 1 mm.
  • the sheet 62 may comprise in its median part and at its upstream end an upwardly projecting flange of smaller axial dimension than the cylindrical flanges of the circumferential ends 70. flange serves to stiffen the sheet and thus raise the frequencies of its own modes of vibration to avoid any phenomenon of resonance of the screen sheet when it is subjected to vibrations during the passage of air and operation of the turbomachine.
  • the axial dimension of this rim may be 2 mm, for example.
  • the integration of the screen plate 62 according to the invention between the outer casing 14 and the wall 16 does not require any structural modification of the compressor 10 since this sheet bears at one end on a flange 54 used for fixing the upstream shell. 52 and is fixed on flanges 42, 44 for securing segments 36, 38.
  • This sheet 62 can thus be mounted in all turbomachines during manufacture or during a maintenance operation.
  • the figure 8 represents the mounting of fixing screws 78 in the holes 72 of the screen plate 62.
  • the presence of a frustoconical wall 68 at the upstream end of the cylindrical wall 62 makes it possible to easily introduce the screws 78 into the holes of the flange 42.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP08168909.3A 2007-12-14 2008-11-12 Vorrichtung zum Luftabzug in einem Kompressor eines Turbotriebwerks Active EP2071192B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0708702A FR2925130B1 (fr) 2007-12-14 2007-12-14 Dispositif de prelevement d'air dans un compresseur de turbomachine

Publications (2)

Publication Number Publication Date
EP2071192A1 true EP2071192A1 (de) 2009-06-17
EP2071192B1 EP2071192B1 (de) 2018-01-03

Family

ID=39706476

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08168909.3A Active EP2071192B1 (de) 2007-12-14 2008-11-12 Vorrichtung zum Luftabzug in einem Kompressor eines Turbotriebwerks

Country Status (6)

Country Link
US (1) US8152460B2 (de)
EP (1) EP2071192B1 (de)
JP (1) JP5474344B2 (de)
CA (1) CA2646935C (de)
FR (1) FR2925130B1 (de)
RU (1) RU2486374C2 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2998330A1 (fr) * 2012-11-20 2014-05-23 Snecma Moyeu de carter pour turbomachine d'aeronef comprenant une piece de fonderie compacte a deflecteur integre au flasque aval

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* Cited by examiner, † Cited by third party
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EP2410138B8 (de) * 2010-07-22 2017-07-19 Ansaldo Energia IP UK Limited Flanschanordnung eines Gasturbinentriebwerks und Verfahren zu deren Nachrüstung
US9528391B2 (en) 2012-07-17 2016-12-27 United Technologies Corporation Gas turbine engine outer case with contoured bleed boss
US9328735B2 (en) 2012-09-28 2016-05-03 United Technologies Corporation Split ring valve
US9677472B2 (en) 2012-10-08 2017-06-13 United Technologies Corporation Bleed air slot
WO2014098936A1 (en) * 2012-12-18 2014-06-26 United Technologies Corporation Gas turbine engine inner case including non-symmetrical bleed slots
US9885247B2 (en) * 2015-05-19 2018-02-06 United Technologies Corporation Support assembly for a gas turbine engine
US10125781B2 (en) * 2015-12-30 2018-11-13 General Electric Company Systems and methods for a compressor diffusion slot
FR3048017B1 (fr) * 2016-02-24 2019-05-31 Safran Aircraft Engines Redresseur pour compresseur de turbomachine d'aeronef, comprenant des orifices de prelevement d'air de forme etiree selon la direction circonferentielle
US20180045218A1 (en) * 2016-08-11 2018-02-15 United Technologies Corporation Shim for gas turbine engine
US11149653B2 (en) * 2018-08-14 2021-10-19 Raytheon Technologies Corporation Bleed valve actuation system having split ring segments and splice bracket

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EP0374004A1 (de) * 1988-12-15 1990-06-20 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Abblasventil eines Triebwerkverdichters
US5380151A (en) * 1993-10-13 1995-01-10 Pratt & Whitney Canada, Inc. Axially opening cylindrical bleed valve
EP0902179A2 (de) * 1997-09-09 1999-03-17 United Technologies Corporation Ablassventilsystem
US20050008476A1 (en) * 2003-07-07 2005-01-13 Andreas Eleftheriou Inflatable compressor bleed valve system
EP1531236A2 (de) * 2003-11-13 2005-05-18 United Technologies Corporation Verdichtergehäuse einer Gasturbine mit Zapfluftöffnungen

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Publication number Priority date Publication date Assignee Title
EP0374004A1 (de) * 1988-12-15 1990-06-20 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Abblasventil eines Triebwerkverdichters
US5380151A (en) * 1993-10-13 1995-01-10 Pratt & Whitney Canada, Inc. Axially opening cylindrical bleed valve
EP0902179A2 (de) * 1997-09-09 1999-03-17 United Technologies Corporation Ablassventilsystem
US20050008476A1 (en) * 2003-07-07 2005-01-13 Andreas Eleftheriou Inflatable compressor bleed valve system
EP1531236A2 (de) * 2003-11-13 2005-05-18 United Technologies Corporation Verdichtergehäuse einer Gasturbine mit Zapfluftöffnungen

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2998330A1 (fr) * 2012-11-20 2014-05-23 Snecma Moyeu de carter pour turbomachine d'aeronef comprenant une piece de fonderie compacte a deflecteur integre au flasque aval

Also Published As

Publication number Publication date
EP2071192B1 (de) 2018-01-03
RU2486374C2 (ru) 2013-06-27
US8152460B2 (en) 2012-04-10
JP2009144714A (ja) 2009-07-02
CA2646935C (fr) 2016-05-03
JP5474344B2 (ja) 2014-04-16
FR2925130A1 (fr) 2009-06-19
US20090155056A1 (en) 2009-06-18
CA2646935A1 (fr) 2009-06-14
FR2925130B1 (fr) 2012-07-27
RU2008149155A (ru) 2010-06-20

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