EP3536974A1 - Compresseur de turbine à gaz - Google Patents

Compresseur de turbine à gaz Download PDF

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Publication number
EP3536974A1
EP3536974A1 EP19159823.4A EP19159823A EP3536974A1 EP 3536974 A1 EP3536974 A1 EP 3536974A1 EP 19159823 A EP19159823 A EP 19159823A EP 3536974 A1 EP3536974 A1 EP 3536974A1
Authority
EP
European Patent Office
Prior art keywords
blade tip
edge
upstream
groove
downstream
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
EP19159823.4A
Other languages
German (de)
English (en)
Other versions
EP3536974B1 (fr
Inventor
Giovanni Brignole
Tobias Mayenberger
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines AG
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 MTU Aero Engines AG filed Critical MTU Aero Engines AG
Publication of EP3536974A1 publication Critical patent/EP3536974A1/fr
Application granted granted Critical
Publication of EP3536974B1 publication Critical patent/EP3536974B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
    • F04D29/526—Details of the casing section radially opposing blade tips
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • 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
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F04D29/685—Inducing localised fluid recirculation in the stator-rotor interface
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/126—Baffles or ribs
    • 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
    • F05D2240/00—Components
    • F05D2240/55—Seals

Definitions

  • the present invention relates to a gas turbine compressor and an aircraft engine with such a gas turbine compressor and a method for designing such a gas turbine compressor.
  • From the EP2927503 Al is a gas turbine compressor having blade tips each having an upstream leading and trailing trailing edge and a blade tip radially opposed flow passage wall known in which a circumferential groove having an upstream and a downstream groove edge is disposed, wherein in the peripheral groove webs are arranged, each having a radial cutback.
  • An object of an embodiment of the present invention is to improve a gas turbine compressor.
  • Claims 10, 11 provide an aircraft engine with a gas turbine compressor described herein or a method for designing a gas turbine compressor described herein under protection.
  • Advantageous embodiments of the invention are the subject of the dependent claims.
  • one, in particular axial, gas turbine compressor has one or more circumferentially juxtaposed blades with, in particular deckband sou, blade tips and this radially opposite flow channel wall.
  • the gas turbine compressor is a gas turbine compressor for an aircraft engine or an aircraft engine; in particular, it may be a low-pressure compressor arranged upstream of another gas turbine compressor in a gas turbine or a high-pressure compressor arranged downstream of another gas turbine compressor.
  • the blades are in a version a rotating rotatably mounted rotor, rotating in operation blades whose radially outer blade tips the housing-fixed flow channel wall radially outwardly opposite.
  • the blades are fixed to the housing vanes, which faces the rotating in operation, rotatably mounted Strömungskanalwandung radially inward.
  • an axial direction is in the usual way parallel to the axis of rotation of the compressor
  • a circumferential direction is a direction of rotation about this axis of rotation and a radial direction perpendicular to the axial and circumferential direction.
  • Upstream and downflow in one embodiment relates to a (normal) flow (direction) of the compressor in a conventional manner, so that in one embodiment upstream of an inlet and downstream of an outlet of the compressor is closer.
  • a circumferential groove is arranged.
  • this has an upstream groove flank which merges into the flow channel wall in an upstream groove edge, a downstream groove flank which merges into a flow channel wall in a downstream groove edge, and a groove base which connects these groove flanks.
  • a groove edge may have a sharp-edged or angular or even rounded or have a radius, in which case the center edge or intersection of its two outermost tangents may define the groove edge for dimensions.
  • the upstream groove flank and / or the downstream groove flank has an axial undercut, the cross-sectional area of which in at least one meridian section in a development is less than 10% of a cross-sectional area of the circumferential groove between its upstream and downstream groove edge.
  • a meridian section in the sense of the present invention is a plane section which contains the axis of rotation of the compressor.
  • An axial undercut of the upstream groove flank is a region of this groove flank which is arranged in the axial direction upstream of the upstream groove edge. Accordingly, one is axial undercut of the downstream groove flank a portion of this groove flank, which is arranged in the axial direction downstream behind the downstream groove edge.
  • a cross-sectional area of the circumferential groove between its upstream and downstream groove edges is correspondingly the area delimited in the meridian section by the groove bottom, a straight connecting line between the upstream and downstream groove edges, and perpendiculars by the upstream and downstream groove edges.
  • the circumferential groove extends in one embodiment, in particular continuously or without interruption, over the full circumference of the flow channel wall or over 360 °.
  • the upstream and downstream groove edges are each a continuous edge that extends uninterrupted 360 °.
  • one or more webs are arranged.
  • a plurality of adjacent, in particular all, webs can be designed identically in one embodiment, in particular, at least substantially, have identical dimensions and contours.
  • the production and / or aerodynamics of the circumferential groove can be improved.
  • adjacent webs can be designed differently in one embodiment, in particular have different dimensions and / or contours.
  • targeted asymmetries can be displayed or compensated in one embodiment.
  • Three or more, in particular all, webs can be spaced equidistantly in the circumferential direction.
  • three or more, in particular all, webs in the circumferential direction in pairs have different distances from each other.
  • a radial pruning means in particular, an empty space between a blade-side end face of the web and its projection into a reference surface which extends from the upstream groove edge to the downstream groove edge, wherein the curvature of the reference surface in the meridian sections through the end face is equal to infinity or to the upstream and downstream groove edge equal to the curvature of the flow channel wall and therebetween in the axial direction is continuously linear.
  • the radial cutback is understood as meaning the free area between a blade tip side upper edge of the cross section of the web and a reference curve extending from the upstream groove edge to the downstream groove edge, the curvature of the reference curve being equal to infinity or at the upstream and downstream groove edge equal to the curvature of the Strömungskanalwandung and between them in the axial direction is continuously linear.
  • a radial cutback in one embodiment is understood to mean the empty space or the free area between the blade-side end face or upper edge of the web and a flow channel contour that is virtually continued across the circumferential groove, wherein this virtually continuous contour is a straight connection plane or the groove edges can connect with a curvature which corresponds to the groove edges of the curvature of the flow channel contour and interpolated linearly therebetween.
  • an axial distance (“axial distance") between an upstream beginning of the cutback and an upstream leading edge of the blade tip is at least 1%, in particular at least 1.5%, in one embodiment at least 2%, and / or at most 40%, in particular at most 30%, in an embodiment at most 15%, a chord length between the upstream leading edge and a downstream trailing edge of the blade tip or the gas turbine compressor is so designed or chosen this axial distance such.
  • an axial distance between the upstream leading edge of the blade tip and the downstream groove edge is at least 5%, in particular at least 7.5% an embodiment of at least 10%, and / or at most 40%, in particular at most 35%, in one embodiment at most 30%, the chord length between the upstream leading edge and the downstream Trailing edge of the blade tip or the gas turbine compressor is designed or chosen this axial distance such.
  • an axial distance between the upstream leading edge of the blade tip and a kink of a blade tip side upper edge of the web in the cutback not more than 10%, in particular at most 7.5%, in one embodiment at most 5%, of the chord length between the upstream leading edge and the downstream trailing edge of the blade tip, in one embodiment the kink is located downstream, in another embodiment the kink is located upstream from the upstream leading edge of the blade tip; .
  • the gas turbine compressor is designed such or chosen this axial distance such.
  • the kink of the blade tip side upper edge may be sharp or square or rounded or have a radius in one embodiment, then for measurements whose center or intersection of its two outermost tangents can define the kink.
  • a discontinuity (sstelle) of the tangent to the upper edge of the web is referred to as a kink.
  • the blade tip-side end face or upper edge of the web can also be kink-free in the cutback.
  • a radial distance between the blade tip and the radially opposite downstream edge of the groove or the gas turbine compressor is designed such or this radial distance chosen such.
  • chord length designates in one embodiment in a customary manner the length of the profile chord or center line of the blade tip or its projection in the axial direction or the axial distance between the leading and trailing edges of the blade tip.
  • an upstream beginning of the cutback axially downstream of the upstream groove edge between said groove edge and the upstream leading edge of the blade tip and / or a downstream end of the cutback disposed at a blade tip nearer half a radial height of the circumferential groove.
  • an upstream start of the cutback is understood to be that axial position beyond which the blade-side end face or upper edge of the web deviates from the virtually continuous flow channel contour or the reference surface or curve away from the blade tip towards the groove bottom.
  • an upstream beginning of the cutback section is understood to be the axial position from which the blade-side end face or upper edge of the web from the straight reference surface or curve in the radial direction to the groove base by at least 1%, in particular at least 5% of a maximum Radial distance between a blade tip closer groove edge and the groove bottom deviates.
  • the upstream beginning of the cutback in one embodiment, is located axially downstream of the upstream groove edge and upstream of the upstream leading edge of the blade tip.
  • the blade-side end face (or in one or more, preferably all, meridian sections through the blade tip side end face of the web, the upper edge) of the web in one embodiment continues the flow channel contour with continuous curvature or without sudden change in curvature.
  • a downstream end of the cutback section is understood to be that axial position at which the blade-side end face or upper edge of the web opens again into the reference surface or curve or into the downstream groove flank.
  • a downstream end of the recut section is understood to be that axial position from which the blade-side end face or upper edge of the web from the straight reference surface or curve to the groove bottom in the radial direction again by less than 5%, in particular less than 1 % of the maximum radial distance between the blade tip closer groove edge and the groove bottom deviates.
  • a radial height of the circumferential groove is in particular a maximum distance between the groove base and the reference surface or curve, in particular a maximum distance between the groove base and the groove edge closer to the blade tip, in the radial direction or in a direction perpendicular to the connecting line understood upstream and downstream groove edge, wherein such a distance perpendicular to the connecting line generalizing is referred to as the radial height of the circumferential groove.
  • the radial pruning terminates in the reference surface, in a further embodiment, axially upstream of or downstream of the upstream leading edge of the blade tip.
  • the blade-side end face (or the upper edge in one or more, preferably all, meridian sections through the blade tip-side end face of the web) sets the flow channel contour with a continuous curvature or without an abrupt change in the curvature from the downstream in one embodiment Groove edge upstream.
  • the radial cutback ends in the radially upper half of the downstream groove flank, the web is continuously cut back radially from the beginning of the cutback.
  • a radially upper half is generally called the part of the downstream groove flank, extending in the radial direction or a direction perpendicular to the connecting line of the upstream and downstream groove edge extends over 50% of the maximum distance of the downstream groove edge from the groove bottom in this direction.
  • the web opens into the upstream and / or the downstream groove flank of the circumferential groove, so it can thus extend in particular axially through the groove or its maximum axial length.
  • a blade tip-side upper edge of the web at the upstream groove edge may have the same curvature as the flow channel contour, i. at the upstream groove edge have a continuous curvature, and continue steadily until the beginning of the re-cut.
  • the web can be straight or curved or run.
  • the blade-side end face of the web at least substantially, open axially into the upstream groove edge. Additionally or alternatively, the blade-side end face in or against a direction of rotation of the blade tip curved into the downstream groove edge open.
  • the surface of the cutback is limited in at least one meridian section to at most 30%, in particular at most 25% of the cross-sectional area of the circumferential groove.
  • the web in one or more, in particular all meridian sections through the blade tip side end face of the web on a cross-sectional area which is at least 70%, in particular at least 75%, the cross-sectional area of the circumferential groove in this meridian section.
  • a cross-sectional area of the circumferential groove is, according to the above-described definition, the area delimited in the meridian section by the groove bottom, the groove flanks and a straight connecting line between the upstream and downstream groove edge.
  • the circumferential groove encloses in one or more, in particular all meridian sections through the blade tip side end face of the web at the upstream edge of the groove with the flow channel wall at an angle which is between 60 ° and 90 °. In this way, in particular, an advantageous axial undercut can be represented.
  • an axial distance between the upstream groove edge and the downstream edge of the blade tip downstream therefrom is greater than an axial distance between the downstream groove edge and the leading edge of the blade tip disposed therefrom.
  • the leading edge of the blade tip is disposed between the upstream and downstream groove edges and closer to the downstream groove edge.
  • an axial distance between the upstream and downstream groove edges is at least 25% of an axial distance between the upstream leading edge and the downstream trailing edge of the blade tip.
  • the web may be straight or curved, wherein it or its tangents may be radial or inclined to the radial direction. Accordingly, in one embodiment in one or more, in particular all sections perpendicular to the axis of rotation of the compressor through the blade tip side end face of the web of the web to the groove bottom of the circumferential groove in the direction of rotation of the blade tip inclined, in particular by at least 25 ° and / or at most 65 ° to the radial direction.
  • Dimensions refer in one embodiment to a component temperature of 20 ° C and / or components without elastic deformation.
  • Fig. 1 shows in a meridian section a part of a gas turbine compressor according to an embodiment of the present invention and a designed according to an embodiment of the present invention gas turbine compressor.
  • the meridian section contains the axis of rotation of the compressor (horizontal in Fig. 1 ), in the Fig. 1 vertical direction is a radial direction.
  • the gas turbine compressor has in the circumferential direction (perpendicular to the plane of the Fig. 1 ) juxtaposed blades with uncovered blade tips, of which in the meridian section of the Fig. 1 a blade tip 10 is partially shown, and a radially outwardly opposite housing fixed flow channel wall 20 on.
  • a circumferential groove is arranged, which has an upstream groove flank 31, which merges into an upstream groove edge 21 in the Strömungskanalwandung, a downstream groove flank 32, which merges in a downstream groove edge 22 in the flow channel wall, and having these groove flanks connecting groove bottom 33.
  • the upstream groove flank has an axial undercut whose cross-sectional area in the meridian section is less than 10% of a cross-sectional area of the circumferential groove between its upstream and downstream groove edges.
  • This cross-sectional area of the circumferential groove between its upstream and downstream groove edge is the area which is in the meridian section of the Fig. 1 is limited by the groove bottom, a straight connecting line 24 between the upstream and downstream groove edge and perpendicular through the upstream and downstream groove edge, which in Fig. 1 dash-dotted lines are indicated, the cross-sectional area of the undercut corresponding to the area between the upstream groove flank 31 and the in Fig. 1 left dotted vertical lines on the connecting line 24th
  • a straight connecting line 24 between the upstream and downstream groove edge 21, 22 is designated. This thus represents a reference curve which extends from the upstream groove edge to the downstream groove edge, their curvature being equal to infinity.
  • Fig. 1 another reference curve, which also extends from the upstream groove edge to the downstream groove edge, wherein the curvature of this reference curve at the upstream and downstream groove edge is equal to the curvature of Strömungskanalwandung and therebetween in the axial direction is continuously linear, ie the curvature of Strömungskanalwandung 20th interpolated linearly between the groove edges 21, 22.
  • This reference curve 23 thus continues the flow channel contour 20 virtually over the circumferential groove.
  • the reference curves 23, 24 each provide a circumferentially extending corresponding reference surface 23, 24 in the meridian section of FIG Fig. 1 by a blade tip-side end face or upper edge 43 of the web 40.
  • the blade-side end face or upper edge 43 also deviates from the straight reference surface or curve 24 toward the groove base by at least 1% of a maximum radial distance between the groove edge 22 closer to the blade tip and the groove base 33.
  • the point or circumferential line 41 thus defines an upstream beginning of a radial cut-back 44 of the web.
  • the blade-side end face or upper edge of the web continues the flow channel contour 20 with a continuous curvature.
  • the point or circumferential line 42 defines a downstream end of the radial cut-back 44, at which the blade-side end or upper edge 43 of the web opens into the downstream groove flank 32.
  • the blade-side end face or upper edge 43 of the web opens again into the reference surface or curve 23. Then, the point or the circumferential line on which or the blade-side end face or upper edge 43 of the web again opens into the reference surface or curve 23, or the point or the circumferential line, from which or the blade-side end face or upper edge of the web of the straight reference surface or curve 24 to the groove bottom 33 again by less than 1% the maximum radial distance between the blade tip closer groove edge 22 and the groove bottom 33 deviates, the downstream end of the radial cutback.
  • the blade-side end face or upper edge of the web, the flow channel contour with continuous curvature of the downstream groove edge 22 upstream continue to this end of the recut, as shown analogously for the region between the upstream groove edge 21 and the upstream beginning 41 of the cutback.
  • the empty space or the free area between the blade-side end face or upper edge 43 of the web and the reference surface or curve 23 thus defines the radial cutback 44 with its upstream end 41 and its downstream end 42.
  • this upstream beginning 41 of the cutback 44 becomes axially downstream (right in FIG Fig. 1 ) from the upstream groove edge 21 between this groove edge 21 and the upstream leading edge 11 of the blade tip 10 and the downstream end 42 of the cutback 44 are located in a blade tip nearer half 34 of a radial height 35 of the circumferential groove.
  • the maximum distance between the groove base 33 and the blade tip closer groove edge 22 in the radial direction (vertically in Fig. 1 ) or, as in Fig. 1 indicated, the maximum distance 35 between the groove base 33 and the blade tip closer groove edge 22 may be defined in a direction perpendicular to the straight connecting line 24 of the upstream and downstream groove edge.
  • the radial cutback ends in the radially upper half 34 of the downstream groove flank 32, the web is continuously cut back radially from the beginning 41.
  • the radially upper half is the part or region of the downstream groove flank 32 which extends in the radial direction or the direction perpendicular to the connecting line 24 of the upstream and downstream groove edge over 50% of the maximum distance of the downstream groove edge 22 from the groove base 33 in this direction ,
  • the web 40 terminates in the upstream and downstream groove flanks 31, 32 of the circumferential groove, thus extending axially through the groove.
  • the blade tip-side end face or upper edge of the web at the upstream groove edge 21 has the same curvature as the flow channel contour 20 and steadily continues it until the beginning 41 of the cut-back 44.
  • the web 40 has an in Fig. 1 hatched indicated cross-sectional area, which is at least 75% of the cross-sectional area of the circumferential groove in this meridian section, which is defined by the groove flanks 31, 32, the groove base 33 and the connecting line 24 between the two groove edges 21, 22.
  • Fig. 1 closes the circumferential groove at the upstream groove edge 21 with the Strömungskanalwandung 20 an angle ⁇ , which is between 60 ° and 90 °.
  • Fig. 1 In the execution of Fig. 1 is an axial distance between the upstream groove edge 21 and the downstream thereof (right in FIG Fig. 1 ) disposed leading edge 11 of the blade tip 10 is greater than an axial distance between the downstream groove edge 22 and the front edge 11 thereof arranged upstream.
  • an axial distance between the upstream and downstream groove edges 21, 22 is at least 25% of an axial distance between the upstream leading edge 11 and a downstream trailing edge 12 of the blade tip 10.
  • S AX is schematically indicated an axial chord length of the blade tip 10, which may equally correspond to the axial distance between the leading and trailing edges 11, 12 or the length of the chord line or center line of the blade tip 10.
  • An axial distance L KOZ between the upstream beginning 41 of the cutback 44 and the upstream leading edge 11 of the blade tip is between 1% and 40%, preferably between 2% and 15%, of this chord length S AX defined in this way.
  • An axial distance L OL between the upstream leading edge 11 of the blade tip and the downstream groove edge 22 is between 5% and 40%, preferably between 10% and 30%, of the chord length S AX .
  • An axial distance ⁇ 45 between the upstream leading edge 11 of the blade tip and a bend 45 of the blade tip side end face or upper edge 43 of the web in the cutback is at most 10%, preferably at most 5%, of the chord length S AX .
  • a radial distance between the blade tip 10 and the blade tip side end face or upper edge 43 of the web in the cutback 44 is between 50% and 1500%, preferably between 100% and 1000%, of a radial distance H GAP between the blade tip 10 and the latter radially opposite one another downstream groove edge 22.
  • H GAP radial distance between the blade tip 10 and the latter radially opposite one another downstream groove edge 22.
  • the minimum radial distance H KOZ between the blade tip 10 and the blade tip-side end face or upper edge 43 indicated likewise a maximum or average distance or distance at the front edge 11 may be used.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP19159823.4A 2018-03-06 2019-02-27 Compresseur de turbine à gaz Active EP3536974B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102018203304.8A DE102018203304A1 (de) 2018-03-06 2018-03-06 Gasturbinenverdichter

Publications (2)

Publication Number Publication Date
EP3536974A1 true EP3536974A1 (fr) 2019-09-11
EP3536974B1 EP3536974B1 (fr) 2024-06-12

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EP19159823.4A Active EP3536974B1 (fr) 2018-03-06 2019-02-27 Compresseur de turbine à gaz

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US (1) US11686207B2 (fr)
EP (1) EP3536974B1 (fr)
DE (1) DE102018203304A1 (fr)

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112685829B (zh) * 2020-12-22 2021-11-02 中国船舶重工集团公司第七0三研究所 一种船舶燃气轮机压气机带槽环式处理机匣设计方法

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2927503A1 (fr) 2014-04-03 2015-10-07 MTU Aero Engines GmbH Compresseur de turbine à gaz, moteur d'avion et méthode de dimensionnement

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Publication number Priority date Publication date Assignee Title
WO2003072910A1 (fr) * 2002-02-28 2003-09-04 Mtu Aero Engines Gmbh Structure de recirculation de turbocompresseurs
AU2003207365A1 (en) 2002-02-28 2003-09-09 Daimlerchrysler Ag Anti-stall tip treatment means for turbo-compressors
US7186072B2 (en) 2002-08-23 2007-03-06 Mtu Aero Engines Gmbh Recirculation structure for a turbocompressor
DE10330084B4 (de) * 2002-08-23 2010-06-10 Mtu Aero Engines Gmbh Rezirkulationsstruktur für Turboverdichter
DE102007056953B4 (de) * 2007-11-27 2015-10-22 Rolls-Royce Deutschland Ltd & Co Kg Strömungsarbeitsmaschine mit Ringkanalwandausnehmung
DE102008011644A1 (de) * 2008-02-28 2009-09-03 Rolls-Royce Deutschland Ltd & Co Kg Gehäusestrukturierung für Axialverdichter im Nabenbereich
DE102008031982A1 (de) * 2008-07-07 2010-01-14 Rolls-Royce Deutschland Ltd & Co Kg Strömungsarbeitsmaschine mit Nut an einem Laufspalt eines Schaufelendes

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2927503A1 (fr) 2014-04-03 2015-10-07 MTU Aero Engines GmbH Compresseur de turbine à gaz, moteur d'avion et méthode de dimensionnement

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EP3536974B1 (fr) 2024-06-12
US20190277152A1 (en) 2019-09-12
DE102018203304A1 (de) 2019-09-12
US11686207B2 (en) 2023-06-27

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