EP2871368B1 - Compresseur de turbine à gaz - Google Patents

Compresseur de turbine à gaz Download PDF

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Publication number
EP2871368B1
EP2871368B1 EP13192464.9A EP13192464A EP2871368B1 EP 2871368 B1 EP2871368 B1 EP 2871368B1 EP 13192464 A EP13192464 A EP 13192464A EP 2871368 B1 EP2871368 B1 EP 2871368B1
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EP
European Patent Office
Prior art keywords
channel wall
gas turbine
upstream
bleed
angle
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.)
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Application number
EP13192464.9A
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German (de)
English (en)
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EP2871368A1 (fr
Inventor
Roland Wunderer
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
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MTU Aero Engines AG
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Filing date
Publication date
Application filed by MTU Aero Engines AG filed Critical MTU Aero Engines AG
Priority to EP13192464.9A priority Critical patent/EP2871368B1/fr
Priority to US14/533,832 priority patent/US10066633B2/en
Publication of EP2871368A1 publication Critical patent/EP2871368A1/fr
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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
    • F04D27/023—Details or means for fluid extraction
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D19/00—Axial-flow pumps
    • 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
    • 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
    • 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
    • F04D29/547—Ducts having a special shape in order to influence fluid flow

Definitions

  • the present invention relates to a gas turbine compressor with a Abblaskanal and a gas turbine, in particular aircraft engine gas turbine with such a gas turbine compressor.
  • the DE 10 2008 014 957 A1 indicates an entrance angle of a flow into a take-off geometry in response to a bleed air amount relative to an amount of air entering a compressor and a hub ratio.
  • the GB 2 388 875 A suggests a curved upstream channel wall.
  • An axially opposed downstream channel wall has two planar sections connected by a radius. Parameter values for a geometry do not take them into focus.
  • the EP 2 110 559 A2 In one embodiment, there is shown a downstream channel wall having two planar sections. It does not take parameter values for a channel geometry into account.
  • the GB 2 192 229 A refers to a ratio of a withdrawal air quantity relative to an amount of air flowing through a compressor in the range between 7 and 10%.
  • An object of an embodiment of the present invention is to provide an improved gas turbine compressor.
  • Claim 8 provides a gas turbine, in particular an aircraft engine gas turbine, with a corresponding gas turbine compressor under protection.
  • Advantageous embodiments of the invention are the subject of the dependent claims.
  • a gas turbine compressor in particular an aircraft engine gas turbine, a guide grid having a plurality of circumferentially distributed vanes and a playpens with a plurality of circumferentially distributed blades on.
  • the guide grid is arranged upstream of at least one further outlet guide grid, in particular in the flow direction last, or in front of a downstream walkway.
  • one or more further running and guide gratings can be arranged between the guide grid and the outlet guide grid.
  • Guiding and playpens are arranged in an annular space, which is intended to be flowed through during operation of a working gas, in particular air.
  • a cross section of the annular space can, at least in sections, converge or, at least substantially, be constant.
  • a radially outer wall of the annular space merges into an upstream channel wall of a blow-off channel.
  • the upstream channel wall continuously merges into the radially outer wall.
  • the radially inner leading edge is offset radially inwardly from the transition of the upstream channel wall into the radially outer wall.
  • the blow-off channel has a blow-off channel outlet.
  • upstream and downstream or upstream and downstream refer to the normal flow direction in the operation of the compressor, in particular an axial direction from the guide grid to the playpen or from a compressor inlet to a compressor outlet.
  • the exhaust duct may be an annular channel in one embodiment, the leading edge extends in the circumferential direction by 360 °. In one embodiment, the leading edge is rounded or has a, in particular constant, radius. In another embodiment, the Abblaskanal on several circumferentially spaced chimneys or separate passages.
  • the Abblaskanal can communicate at its Abblaskanalaustritt with a, in particular annular, plenum, in particular, continue to continue in operation from the compressor tapped gas, for example for component cooling or the like.
  • the blow-off channel communicates with an inflow channel, which in turn can communicate with the plenum.
  • the downstream channel wall in the meridian section with an axis of rotation of the compressor includes an angle which increases in the direction of flow, in particular continuously or continuously, which is referred to below as the first angle.
  • the bleed flow can be performed loss in one embodiment. Additionally or alternatively, losses of the main flow in the annular space downstream of the leading edge can thereby also be reduced.
  • the first angle increases from the leading edge, in particular to a radius of a rounded leading edge, in the direction of flow.
  • the bleeding of the flow at the Abblaskanaleintritt be improved.
  • the first angle in one embodiment in the flow direction increases monotonously, in particular strictly monotonously.
  • the downstream channel wall is curved in sections or over its entire length.
  • the downstream channel wall can have an at least substantially constant radius of curvature or an at least substantially constant curvature in sections or over its entire length.
  • a curvature of the downstream channel wall in sections or over its entire length increase or decrease or decrease or increase their radius of curvature.
  • the first angle at the Abblaskanalaustritt greater than 30 °, in particular greater than 40 °.
  • the bleed flow can be carried out loss in one embodiment.
  • the upstream channel wall also includes in the meridian section with the axis of rotation an angle which increases in the direction of flow, which is referred to below as the second angle.
  • the second angle increases from the transition of the upstream channel wall in the radially outer wall of the annular space in the direction of flow, in a development, the upstream channel wall is tangentially into the radially outer wall.
  • the second angle in one embodiment in the flow direction increases monotonously, in particular strictly monotonously.
  • the upstream channel wall is curved in sections or over its entire length.
  • the upstream channel wall may in one embodiment in sections or over its entire Have length one, at least substantially, constant radius of curvature or at least substantially constant curvature.
  • a curvature of the upstream channel wall in sections or over its entire length increase or decrease or decrease or increase their radius of curvature.
  • p (x) denotes a radial coordinate of a channel wall, in particular its radially innermost extent or its radially innermost point, at an axial position x
  • the angle of a channel wall with the axis of rotation in one embodiment is understood to mean the angle of a tangent to the channel wall with the axis of rotation.
  • the upstream channel wall sections or over its entire length be more curved than the downstream channel wall, so that the Abblaskanal diverges in one embodiment in sections or over its entire length.
  • the exhaust duct runs in sections or over its entire length from the radially outer wall of the annular space radially outward or away from the axis of rotation. Accordingly, in one embodiment, the first and / or second angle increasing in the flow direction from the axis of rotation to the downstream or upstream channel wall is always greater than zero. If, in one embodiment, the radially outer wall of the annular space converges in the direction of flow, the first and / or second angle may be negative in a development on the radially outer wall of the annular space and positive in the direction of flow.
  • the upstream channel wall transitions downstream from a trailing edge of the guide grid into the annulus. In another embodiment, the upstream channel wall transitions upstream from a trailing edge of the guide grid into the annulus. In other words, the blow-off channel is in this other one
  • the trailing edge is monotonically, in particular strictly monotone, increasingly inclined to the suction side.
  • the trailing edge is bent at least in the radially outer 20%, in particular 15%, the Leitgitter- or Leitschaufelblattt assume in the circumferential direction to the suction side.
  • This bending can be done in one embodiment by rotating the entire stator blade profile or by changing the blade curvature in the trailing edge region.
  • the vane (s), at least in a radially outer region or the vicinity of the Abblaskanals be shortened.
  • the trailing edge may include an angle with the upstream channel wall that is between 60 ° and 120 °, in particular between 75 ° and 105 °, measured in the axial direction or with respect to the projection in the meridian plane.
  • the tapped flow can be performed with even less loss. Additionally or alternatively, losses of the main flow in the annular space downstream of the leading edge can thereby be further reduced.
  • b 1 is first determined according to at least one of the equations (1) - (2 '), and in a further development, further variables, in particular r K , H, L, b 2 and / or s, according to one of the equations (3 ) - (7 ') derived.
  • Fig. 1 shows a portion of a gas turbine compressor of an aircraft engine gas turbine according to an embodiment of the present invention in a meridian section. This has a guide grid with a plurality of circumferentially distributed guide vanes 1 and a playpen with a plurality of circumferentially distributed blades 2.
  • the guide grid is arranged upstream of the downstream walkway and a further, in particular in the flow direction x last exit guide grille (not shown).
  • One or more further running and guide gratings may be arranged between the illustrated guide grid and the outlet guide grid (not shown).
  • Guiding and playpens are arranged in an annular space 5, which is intended to be flowed through during operation of compressed air.
  • a radially outer wall (top in Fig. 1 ) of the annular space is at a transition 4 continuously or without offset in an upstream channel wall 3.1 of a Abblaskanals 3 via.
  • Axially opposite the Abblaskanal a downstream channel wall 3.2 with a radially inner, rounded leading edge 3.3, which is offset from the transition 4 radially inward.
  • At an end remote from the annular space (at the top in FIG Fig. 1 ) has the Abblaskanal 3 a Abblaskanalaustritt.
  • the Abblaskanal communicates at its Abblaskanalaustritt with a plenum (not shown). Likewise, it can also communicate with an inflow channel, which in turn can communicate with the plenum.
  • the downstream channel wall 3.2 closes with a rotational axis of the compressor (horizontal in Fig. 1 ) a strictly monotonically increasing in the flow direction x from the leading edge 3.3 first angle ⁇ , in other words is curved over its entire length (d ⁇ / dx> 0).
  • the upstream channel wall 3.1 includes with the axis of rotation in the flow direction from the transition 4 strictly monotonically increasing second angle ⁇ , is with In other words, also curved over its entire length (d ⁇ / dx> 0), wherein the upstream channel wall merges tangentially into the radially outer wall of the annular space 5.
  • the upstream channel wall is in the execution of Fig. 1 downstream (right) of the trailing edges 1.1 of the guide vanes of the guide grid 1 in the radially outer wall of the annular space 5 via.
  • Fig. 4 shows a view of a trailing edge 1.1 of a guide vane of the guide grid 1 against the flow direction (ie from the right in Fig. 1 ).
  • the trailing edges 1.1 are at least in the radially outer 20%, in particular 15% of Leitgitter- or Leitschaufelblatt Exercise (Rr) (see. Fig. 1 ) in the circumferential direction from a pressure side PS away to a suction side SS of the guide blade toward strictly monotonically increasingly inclined, in other words bent to the suction side SS.
  • Rr Leitgitter- or Leitschaufelblatt Exercise
  • Fig. 3 shows in an enlarged section of the Fig. 1 in particular the blow-off duct with several sizes.
  • b 1 denotes the channel height at the leading edge 3.3, in particular the distance or the shortest distance between the leading edge 3.3 and upstream channel wall 3.1, R or r the outer or inner radius of the annular space at the transition 4 of the upstream channel wall 3.1 in the radially outer Wall of the annular space 5 (see. Fig.
  • R K denotes the radius of curvature of the upstream channel wall 3.1
  • H is the radial distance between the leading edge 3.3 and the junction 4 of the annular space 5 in the upstream channel wall 3.1
  • L is the axial distance between the leading edge 3.3 and the junction 4 of the annular space 5 in the upstream Channel wall 3.1
  • b 2 the outlet channel height at the Abblaskanalaustritt and s the length of the downstream channel wall 3.2 between the leading edge 3.3 and the Abblaskanalaustritt.
  • Fig. 2 shows in Fig. 1 Similarly, a portion of a gas turbine compressor of an aircraft engine gas turbine according to an embodiment of the present invention. Corresponding features are denoted by identical reference numerals, so that the description of the embodiment of Fig. 1 Referred to below and will be discussed only for differences to this.
  • the upstream channel wall 3.1 goes upstream (left) from the trailing edge 1.1 of the guide grid in the radially outer wall of the annular space 5, the axially upstream upstream of the leading edge 3.3 is arranged.
  • the exhaust duct 3 in the embodiment of Fig. 2 partially arranged in the guide grid.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (8)

  1. Compresseur de turbine à gaz doté d'une grille de guidage (1), d'une grille passerelle (2), en particulier vers l'aval, et d'un canal de prélèvement (3) comportant une paroi de conduit (3.1) vers l'amont passant dans un espace annulaire (5), une paroi de conduit (3.2) axialement opposée vers l'aval dotée d'un bord d'attaque (3.3), en particulier arrondi, et une sortie de canal de prélèvement,
    dans lequel la paroi de conduit vers l'aval forme dans la section méridienne un premier angle (α) avec un axe de rotation du compresseur, s'ouvrant dans la direction de l'écoulement (x) ;
    et dans lequel la paroi de conduit vers l'amont forme dans la section méridienne un deuxième angle (β) avec l'axe de rotation, s'ouvrant dans la direction de l'écoulement,
    caractérisé en ce que la paroi de conduit vers l'aval est agencée en aval d'un bord arrière (1.1) de la grille de guidage; et le deuxième angle dans la direction de l'écoulement s'ouvre plus fortement que le premier.
  2. Compresseur de turbine à gaz selon la revendication précédente, caractérisé en ce que le premier angle s'ouvre à partir du bord d'attaque et/ou de façon uniforme, en particulier strictement uniforme.
  3. Compresseur de turbine à gaz selon l'une des revendications précédentes, caractérisé en ce que le premier angle est supérieur à 30º à la sortie du canal de prélèvement.
  4. Compresseur de turbine à gaz selon l'une des revendications précédentes, caractérisé en ce que le deuxième angle s'ouvre de façon uniforme dans la direction de l'écoulement.
  5. Compresseur de turbine à gaz selon l'une des revendications précédentes, caractérisé en ce que la paroi de conduit vers l'amont passe dans l'espace annulaire en amont ou en aval du bord arrière (1.1) de la grille de guidage.
  6. Compresseur de turbine à gaz selon l'une des revendications précédentes,
    caractérisé en ce qu'un bord arrière (1.1) d'au moins une aube directrice de la grille de guidage au moins dans un tiers radialement externe d'une hauteur de grille de guidage, en particulier s'ouvrant de façon uniforme, est incliné dans la direction circonférentielle vers une face d'aspiration de l'aube directrice et/ou est décalé vers l'amont et/ou forme un angle avec la paroi de conduit vers l'amont compris entre 60° et 120°.
  7. Compresseur de turbine à gaz selon l'une des revendications précédentes, caractérisé en ce que s'applique : 0,3 ⋅ m Bleed / m in ⋅ R 2 − r 2 / R ≤ b 1 ≤ 0,7 ⋅ m Bleed / m in ⋅ R 2 − r 2 / R ;
    Figure imgb0023
     et/ou b 1 ≤ r K / 5 ;
    Figure imgb0024
     et/ou 0,8 ⋅ r K + b 1 2 − r K + H 2 1 / 2 ≤ L ≤ 1,2 ⋅ r K + b 1 2 − r K + H 2 1 / 2 ;
    Figure imgb0025
     et/ou b 1 ≥ 0,5 ⋅ b 2 ;
    Figure imgb0026
     et/ou b 2 − b 1 / s ≤ 0,2
    Figure imgb0027
     avec b1 la hauteur de canal d'entrée au bord d'attaque, min le débit massique dans l'afflux de la grille de guidage, mBleed le débit massique dans le canal de prélèvement, R le rayon extérieur de l'espace annulaire, r le rayon intérieur de l'espace annulaire, rK le rayon de courbure de la paroi de conduit vers l'amont, H l'écart radial entre le bord d'attaque et le passage de l'espace annulaire dans la paroi de conduit vers l'amont, L l'écart axial entre le bord d'attaque et le passage de l'espace annulaire dans la paroi de conduit vers l'amont, b2 la hauteur de canal de sortie à la sortie du canal de prélèvement et s la longueur de la paroi de conduit vers l'aval entre le bord d'attaque et la sortie du canal de prélèvement.
  8. Turbine à gaz, en particulier turbine à gaz de moteur d'avion, caractérisée par un compresseur de turbine à gaz selon l'une des revendications précédentes.
EP13192464.9A 2013-11-12 2013-11-12 Compresseur de turbine à gaz Active EP2871368B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP13192464.9A EP2871368B1 (fr) 2013-11-12 2013-11-12 Compresseur de turbine à gaz
US14/533,832 US10066633B2 (en) 2013-11-12 2014-11-05 Gas turbine compressor bleed channel

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP13192464.9A EP2871368B1 (fr) 2013-11-12 2013-11-12 Compresseur de turbine à gaz

Publications (2)

Publication Number Publication Date
EP2871368A1 EP2871368A1 (fr) 2015-05-13
EP2871368B1 true EP2871368B1 (fr) 2018-09-12

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EP13192464.9A Active EP2871368B1 (fr) 2013-11-12 2013-11-12 Compresseur de turbine à gaz

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US (1) US10066633B2 (fr)
EP (1) EP2871368B1 (fr)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10125781B2 (en) * 2015-12-30 2018-11-13 General Electric Company Systems and methods for a compressor diffusion slot
US10227930B2 (en) * 2016-03-28 2019-03-12 General Electric Company Compressor bleed systems in turbomachines and methods of extracting compressor airflow
US20180313364A1 (en) * 2017-04-27 2018-11-01 General Electric Company Compressor apparatus with bleed slot including turning vanes
US10934943B2 (en) * 2017-04-27 2021-03-02 General Electric Company Compressor apparatus with bleed slot and supplemental flange

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Publication number Priority date Publication date Assignee Title
GB2192229B (en) * 1986-07-04 1990-05-02 Rolls Royce Plc A compressor and air bleed system
US5155993A (en) 1990-04-09 1992-10-20 General Electric Company Apparatus for compressor air extraction
US6109868A (en) * 1998-12-07 2000-08-29 General Electric Company Reduced-length high flow interstage air extraction
JP2002349498A (ja) * 2001-05-24 2002-12-04 Ishikawajima Harima Heavy Ind Co Ltd 低騒音ファン静翼
GB0206880D0 (en) * 2002-03-23 2002-05-01 Rolls Royce Plc A vane for a rotor arrangement for a gas turbine engine
US6783324B2 (en) 2002-08-15 2004-08-31 General Electric Company Compressor bleed case
US7249929B2 (en) * 2003-11-13 2007-07-31 United Technologies Corporation Bleed housing
DE102008014957A1 (de) * 2008-03-19 2009-09-24 Rolls-Royce Deutschland Ltd & Co Kg Gasturbinenverdichter mit Zapfluftentnahme
DE102008019603A1 (de) 2008-04-18 2009-10-22 Rolls-Royce Deutschland Ltd & Co Kg Strömungsmaschine mit schaufelreiheninterner Fluid-Rückführung
FR2970302B1 (fr) * 2011-01-11 2015-07-17 Snecma Turboreacteur a double flux

Non-Patent Citations (1)

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None *

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US20150132115A1 (en) 2015-05-14
EP2871368A1 (fr) 2015-05-13
US10066633B2 (en) 2018-09-04

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