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EP2329150B1 - Turbomachine axial à grille de guidage d'entrée du compresseur asymétrique - Google Patents

Turbomachine axial à grille de guidage d'entrée du compresseur asymétrique Download PDF

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Publication number
EP2329150B1
EP2329150B1 EP09737335.1A EP09737335A EP2329150B1 EP 2329150 B1 EP2329150 B1 EP 2329150B1 EP 09737335 A EP09737335 A EP 09737335A EP 2329150 B1 EP2329150 B1 EP 2329150B1
Authority
EP
European Patent Office
Prior art keywords
guide
guide vanes
different
attack
inlet
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.)
Active
Application number
EP09737335.1A
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German (de)
English (en)
Other versions
EP2329150A1 (fr
Inventor
Sergio Elorza Gomez
Alexander Halcoussis
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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Application filed by MTU Aero Engines AG filed Critical MTU Aero Engines AG
Publication of EP2329150A1 publication Critical patent/EP2329150A1/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
    • 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
    • F04D29/544—Blade shapes

Definitions

  • the invention relates to an axial flow machine with an asymmetrical air inlet and a compressor directly downstream of the air inlet with a guide vanes formed from inlet guide.
  • Such axial flow machine with asymmetric air intake occur, for example, in the core engines of turboprop or helicopter engines.
  • flow problems of the first compressor stage can result, which can lead to a partial detachment of the flow at this blade stage with consequent pumping and loss of efficiency.
  • the invention is therefore based on the object to avoid the disadvantages of the known solutions of the prior art and to provide an improved solution for increasing the stability of an axial flow machine with asymmetric air inlet available.
  • an axial flow machine with an asymmetrical air inlet and a compressor arranged downstream of the air inlet is provided with guide vanes formed exactlysleitgitter in which at least individual guide vanes of successivesleitgitters deviating from the other vanes blade profile and / or have a different angle of attack.
  • the inlet flow angle of the first compressor stage is made uniform in terms of circumference. This takes place in that the different entry angles caused by the asymmetry of the air inlet at different circumferential positions of the inlet guide grid are influenced by targeted profiling and / or targeted change of the angle of attack of individual guide vanes, resulting in a circumferentially symmetrical outflow angle from the inlet guide ring.
  • the peripheral disturbances caused by the asymmetrical air inlet are minimized and thus the first compressor stage largely passes on circumferentially symmetrical inlet conditions, which leads to improved stability and improved efficiency of the compressor.
  • An advantageous embodiment of the invention provides that one or more of the guide gratings following the inlet guide grille have at least individual guide vanes with a blade profile deviating from the remaining guide vanes and / or a different angle of attack.
  • An advantageous embodiment of the invention provides that individual vane groups have a blade profile deviating from the remaining vanes and / or angle of attack. This allows a rational production and corresponding cost savings.
  • the guide vanes may be arranged in several groups of different geometry.
  • a further advantageous embodiment of the invention provides that the guide vanes of the respective vanes groups have mutually differing blade profiles and / or angle of attack.
  • a further advantageous embodiment of the invention provides that all guide vanes are profiled differently and / or have a different angle of attack. That Here, a targeted profiling of each blade or a staggering of the individual blades can be done and thereby made an adjustment to the asymmetric flow
  • a further advantageous embodiment of the invention provides that the guide vanes are designed to be adjustable. By a different adjustment of at least individual blades or blade groups also the desired effect can be achieved, since this can be done quasi a targeted rescaling of individual blades. This has the further advantage that with changed flow conditions, the individual alignment of the guide grid can be traced.
  • a further advantageous embodiment of the invention provides that the guide vanes are formed on the inlet side of a fixed part and the outlet side of a pivotable part.
  • a further advantageous embodiment of the invention provides that an individual control is provided for each or all vanes. This enables individual descendants of each individual blade under changed flow conditions.
  • FIG. 1 shows a schematic representation of a developed constructivesleitgitters according to the present invention with multi-profiles, ie individual profiling of each blade of the ensuresleitgitters.
  • the blades are adapted to the variable circumferentially asymmetrical angle of attack of the inlet guide grille. This unbalanced flow is caused by the asymmetric air inlet.
  • a constant outflow angle is generated over the entire circumference and the first compressor stage passed largely circumferentially symmetrical entry conditions. This leads to improved stability and improved efficiency of the compressor.
  • FIG. 2 Figure 12 is a schematic representation of a prior art unwound inlet guide grate with circumferentially asymmetric flow caused by an asymmetric air inlet.
  • the leftmost and outermost right vane in the plane of the drawing have separations which continue in the subsequent compressor stages and lead to unstable compressor behavior, ie to pumps.
  • FIG. 2 It can be seen that the outflow angle in this case is not constant over the circumference, but changes at each vane, which can also lead to unstable compressor behavior and efficiency losses.

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

Claims (8)

  1. Moteur à turbopropulsion ou d'hélicoptère comportant une entrée d'air asymétrique et un compresseur en aval de l'entrée d'air, comportant une grille de guidage d'entrée formée de pales directrices, caractérisé en ce qu'au moins certaines pales directrices de la grille de guidage d'entrée présentent un profil de pale différent des autres pales directrices et/ou un angle d'attaque ; de telle sorte qu'un angle de fuite constant est créé sur toute la surface de la grille de guidage d'entrée.
  2. Moteur à turbopropulsion ou d'hélicoptère selon la revendication 1, caractérisé en ce que certaines des grilles de guidage suivant la grille de guidage d'entrée ou plusieurs d'entre elles présentent au moins certaines pales de guidage qui ont un profil de pale différent des autres pales de guidage et/ou un angle d'attaque différent.
  3. Moteur à turbopropulsionn ou d'hélicoptère selon la revendication 1 ou 2, caractérisé en ce que certains groupes de pales de guidage présentent un profil de pale différent des autres pales de guidage et/ou un angle d'attaque différent.
  4. Moteur à turbopropulsion ou d'hélicoptère selon la revendication 3, caractérisé en ce que les pales directrices de chaque groupe de pales directrices présentent des profils de pale et/ou des angles d'attaque différents les uns des autres.
  5. Moteur à turbopropulsion ou d'hélicoptère selon l'une des revendications 1 à 4, caractérisé en ce que toutes les pales directrices sont profilées différemment et/ou présentent un angle d'attaque différent.
  6. Moteur à turbopropulsion ou d'hélicoptère selon les revendications 1 à 5, caractérisé en ce que les pales directrices sont conçues de manière réglable.
  7. Moteur à turbopropulsion ou d'hélicoptère selon les revendications 1 à 6, caractérisé en ce que les pales directrices sont formées dans une partie fixe côté entrée et dans une partie pivotante côté sortie.
  8. Moteur à turbopropulsion ou d'hélicoptère selon les revendications 6 ou 7, caractérisé en ce qu'une régulation individuelle est prévue respectivement pour certaines ou l'ensemble des pales directrices.
EP09737335.1A 2008-09-29 2009-09-09 Turbomachine axial à grille de guidage d'entrée du compresseur asymétrique Active EP2329150B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102008049358A DE102008049358A1 (de) 2008-09-29 2008-09-29 Axiale Strömungsmaschine mit asymmetrischem Verdichtereintrittsleitgitter
PCT/DE2009/001281 WO2010034285A1 (fr) 2008-09-29 2009-09-09 Turbomachine axial à grille de guidage d'entrée du compresseur asymétrique

Publications (2)

Publication Number Publication Date
EP2329150A1 EP2329150A1 (fr) 2011-06-08
EP2329150B1 true EP2329150B1 (fr) 2018-03-21

Family

ID=41650309

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09737335.1A Active EP2329150B1 (fr) 2008-09-29 2009-09-09 Turbomachine axial à grille de guidage d'entrée du compresseur asymétrique

Country Status (6)

Country Link
US (1) US20110164967A1 (fr)
EP (1) EP2329150B1 (fr)
CN (1) CN102165198A (fr)
CA (1) CA2738201A1 (fr)
DE (1) DE102008049358A1 (fr)
WO (1) WO2010034285A1 (fr)

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US20110110763A1 (en) * 2009-11-06 2011-05-12 Dresser-Rand Company Exhaust Ring and Method to Reduce Turbine Acoustic Signature
GB201115581D0 (en) 2011-09-09 2011-10-26 Rolls Royce Plc A turbine engine stator and method of assembly of the same
EP2623793B1 (fr) 2012-02-02 2016-08-10 MTU Aero Engines GmbH Turbomachine avec grille d'aubes
US9194301B2 (en) * 2012-06-04 2015-11-24 United Technologies Corporation Protecting the operating margin of a gas turbine engine having variable vanes from aerodynamic distortion
JP6097194B2 (ja) * 2013-10-09 2017-03-15 三菱重工業株式会社 空気機械
US20150198163A1 (en) * 2014-01-15 2015-07-16 Honeywell International Inc. Turbocharger With Twin Parallel Compressor Impellers And Having Center Housing Features For Conditioning Flow In The Rear Impeller
US10145301B2 (en) 2014-09-23 2018-12-04 Pratt & Whitney Canada Corp. Gas turbine engine inlet
US10378554B2 (en) * 2014-09-23 2019-08-13 Pratt & Whitney Canada Corp. Gas turbine engine with partial inlet vane
US9938848B2 (en) 2015-04-23 2018-04-10 Pratt & Whitney Canada Corp. Rotor assembly with wear member
US9957807B2 (en) 2015-04-23 2018-05-01 Pratt & Whitney Canada Corp. Rotor assembly with scoop
FR3040448B1 (fr) * 2015-09-02 2018-07-13 Safran Aircraft Engines Piece d'etage redresseur de flux secondaire d'une turbomachine a double flux
PL415534A1 (pl) 2016-01-04 2017-07-17 General Electric Company Układ dla zespołu osłony i przegrody wstępnych łopatek kierowniczych
US10259565B2 (en) 2016-08-11 2019-04-16 General Electric Company Inlet assembly for an aircraft aft fan
US10704418B2 (en) 2016-08-11 2020-07-07 General Electric Company Inlet assembly for an aircraft aft fan
US10252790B2 (en) 2016-08-11 2019-04-09 General Electric Company Inlet assembly for an aircraft aft fan
US10253779B2 (en) 2016-08-11 2019-04-09 General Electric Company Inlet guide vane assembly for reducing airflow swirl distortion of an aircraft aft fan
US10724540B2 (en) 2016-12-06 2020-07-28 Pratt & Whitney Canada Corp. Stator for a gas turbine engine fan
US10690146B2 (en) 2017-01-05 2020-06-23 Pratt & Whitney Canada Corp. Turbofan nacelle assembly with flow disruptor
CN107420349B (zh) * 2017-09-14 2019-03-01 西安交通大学 一种预旋条件下低流动损失的离心压缩机进口导叶结构的设计方法
FR3081521B1 (fr) * 2018-05-24 2021-05-14 Safran Aircraft Engines Aube de turbomachine dont des sections presentent une portion aval d'epaisseur reduite
CN113944655B (zh) * 2020-07-17 2023-07-07 广东美的白色家电技术创新中心有限公司 一种吸尘器的导流装置及吸尘器

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FR2205927A5 (fr) * 1972-11-08 1974-05-31 Bertin & Cie
US3861822A (en) * 1974-02-27 1975-01-21 Gen Electric Duct with vanes having selectively variable pitch
GB2046849A (en) * 1979-04-17 1980-11-19 Rolls Royse Ltd Turbomachine strut
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DE10053361C1 (de) * 2000-10-27 2002-06-06 Mtu Aero Engines Gmbh Schaufelgitteranordnung für Turbomaschinen
JP2004100553A (ja) * 2002-09-09 2004-04-02 Mitsubishi Heavy Ind Ltd 回転機械の静翼構造
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EP1508669B1 (fr) * 2003-08-19 2007-03-21 Siemens Aktiengesellschaft Diaphragme pour compresseur et turbine
KR101070903B1 (ko) * 2004-08-19 2011-10-06 삼성테크윈 주식회사 가변 베인형 터빈
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Also Published As

Publication number Publication date
US20110164967A1 (en) 2011-07-07
WO2010034285A1 (fr) 2010-04-01
CN102165198A (zh) 2011-08-24
EP2329150A1 (fr) 2011-06-08
DE102008049358A1 (de) 2010-04-01
CA2738201A1 (fr) 2010-04-01

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