EP1277967B1 - Structure de boítier de compresseur - Google Patents

Structure de boítier de compresseur Download PDF

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Publication number
EP1277967B1
EP1277967B1 EP02013280A EP02013280A EP1277967B1 EP 1277967 B1 EP1277967 B1 EP 1277967B1 EP 02013280 A EP02013280 A EP 02013280A EP 02013280 A EP02013280 A EP 02013280A EP 1277967 B1 EP1277967 B1 EP 1277967B1
Authority
EP
European Patent Office
Prior art keywords
groove
grooves
housing structure
compressor housing
cross sections
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.)
Expired - Lifetime
Application number
EP02013280A
Other languages
German (de)
English (en)
Other versions
EP1277967A1 (fr
Inventor
Jürgen Schmücker
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 GmbH
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 GmbH filed Critical MTU Aero Engines GmbH
Publication of EP1277967A1 publication Critical patent/EP1277967A1/fr
Application granted granted Critical
Publication of EP1277967B1 publication Critical patent/EP1277967B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • 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
    • 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

Definitions

  • the invention relates to a compressor housing structure in the region of an axially flowed through Blade ring, with a plurality of uniformly distributed over the housing periphery, to the blade tips open towards and at least approximately axially extending grooves, according to the preamble of claim 1.
  • a compressor housing structure of this type is known for example from DE 35 21 1 798 C2 known and has the primary task, with increasing throttling in partial load or full load raise the pumping limit to allow safe operation without pumps or to allow an increase in the available work area.
  • the grooves act as recirculation channels for high pressure accumulated air in the air External area of the blade ring without recirculation option to "rotating stall" and pumps would lead.
  • the upstream, front groove ends upstream of the blade tip entry edges see dimension A in Figures 2, 8, 9 and 10
  • the rear groove ends lie in the radial plane of the blade tip exit edges or rather in front of this radial plane.
  • Figure 4 of this patent is provided in to arrange straight grooves in the circumferential direction inclined so that the air inlet their downstream ends is facilitated (see also claim 2).
  • EP 0 497 574 B1 protects a fan case treatment which is arranged above the blade tips of a low-pressure compressor.
  • This structure includes axially spaced inlet and outlet passages (34, 36) and inlet and outlet ports, respectively (56,58) and vanes (38,66) in the connecting passages between Inlet and outlet.
  • the recirculation air entering the structure with significant circumferential component is deflected by the vanes so that they pass through the outlet in predominantly axial direction is returned to the main flow, i. largely without Circumferential component. Without this change or reduction of the perimeter component would hit the air with counter-rotation on the blade tips, i.
  • the object of the invention is a compressor housing structure which is based on the principle of air or gas recirculation and at simple, inexpensive construction a significant increase in the surge limit of a Compressor and thus a noticeable increase in his work area by fluidic Optimization possible.
  • the groove cross sections so inclined that the entry of the recirculation air is facilitated, the Inclination from the opening to the groove bottom a circumferential component in the direction of rotation, i.e. has in the direction of movement of the blade tips.
  • the inclination is reversed, so that the recirculation air exiting here in the main flow with a direct spin on the rotating blade tips hits what the flow significantly improved and reduced losses. Also the tendency to flow separation is noticeably reduced.
  • the compressor housing structure 1 has a plurality of evenly over the circumference of the housing distributed grooves 2, which extends from an upstream radial plane Eo up to a downstream radial plane egg extend.
  • an upstream radial plane Eo up to a downstream radial plane egg extend In the right, lower part of Figure 1 is to detect the tip 8 of a blade of a blade ring 7, wherein accordingly the flow direction (large white arrow) the blade tip leading edge 9 left, the Vane tip exit edge 10 is right.
  • the direction of movement D of the blade tip 8 is indicated by a cross in a circle, the peripheral component of the corresponding Rotational motion should therefore point to the back starting from the plane of the drawing.
  • Radial plane Eo i. the front end of the groove lies clearly upstream of the blade tip leading edge 9, the radial plane Ei, i.
  • each groove 2 is according to the invention from its front, upstream to its rear, continuously twisted (twisted) downstream end, the drill axis a imaginary, axial straight line in the annular space contour R is.
  • the annular space contour R is in the groove area usually circular cylindrical, in rare cases, it can be appropriate slightly taper or widen a circular cone.
  • the opening 3 of each groove thus has an at least largely axial center line / axis of symmetry.
  • the eye-catching, mirror-symmetrical and bell-like section line in Figure 1 results from the Section of a radial-axial plane with the spatially twisted groove contour.
  • the dashed Groove contour, in particular the groove bottom 6, right above the "bell line” is behind the plane of the drawing, whereas the dash-dotted groove contour on the left above the "bell line” lies in front of the drawing plane.
  • At the highest point of the "bell line” lies the middle the Nutgrundes 6 exactly in the plane of the drawing, as well as the imaginary center line of the corresponding groove cross-section.
  • the opening 3 of each groove 2 may be in its axially middle Be covered area by an annular circumferential ridge 11, the inner diameter aligned with the annular space contour R. This can have advantages in the sense of lesser Friction, turbulence, etc. result.
  • FIG. 2 corresponds to a radial section / cross section according to the course A-A in FIG. 1.
  • the blade tip 8 can be seen with its direction of movement D (arrow to the left) and with its leading edge 9 and its trailing edge 10 short distance above the blade tip contour is the annular space contour R as a circular arc line recognizable.
  • the vertical, dot-dashed and unspecified axis through the point S corresponds to the radial direction, starting from the blade ring center.
  • the laterally inclined axes M, Mi and Mo correspond to imaginary central axes of Nutquerroughe at axially different locations of the groove length.
  • the central axes M, Mi, Mo all groove cross sections under different Inclination angles ⁇ , ⁇ i, ⁇ o intersect the annular space contour in an axial straight line, so that S is not just an intersection, but a straight, axial intersection and at the same time the axis of symmetry of the opening 3 of the groove 2. S is therefore also the imaginary Center of twisting / twisting.
  • the path of the recirculation flow through the groove 2 is also indicated here with small white arrows.
  • the flow entry at the rear Nutende takes place approximately at the angle ⁇ i with a peripheral component in the direction of movement the blade tips 8.
  • the flow outlet at the front groove end is about at the angle ⁇ o in the sense of a constant spin with the blade rotation.
  • the groove depth can vary over the axial Nuterstreckung, in particular a reduction the depth to the two groove ends is conceivable.
  • the exact definition of Groove geometries including inclination angles are likely to require appropriate Calculations and experiments.
  • FIG. 2 only one groove 2 is shown for the sake of clarity. Actually the grooves are relatively close in the circumferential direction, the remaining wall thicknesses between the grooves may be smaller than the clear distance between the side walls the grooves. In Figure 2 would therefore be real about 4 to 5 grooves next to each other recognizable be.

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

Claims (7)

  1. Structure de carter de compresseur dans la zone d'une couronne des aubes mobiles à circulation axiale, avec une pluralité de rainures réparties uniformément sur le pourtour du carter, ouvertes vers les extrémités des aubes et s'étendant au moins approximativement axialement, qui s'étendent entre un premier plan radial en amont des arêtes d'attaque des extrémités des aubes et un second plan radial entre les arêtes d'attaque des extrémités des aubes et les arêtes de sortie des extrémités des aubes et qui -respectivement en coupe radiale- comportent des sections transversales de rainures avec des parois latérales droites et parallèles sur la majeure partie de leur profondeur, caractérisée en ce que les axes médians (Mo) - imaginaires- des sections transversales de rainures présentent, au niveau des extrémités de rainures situées en amont -à partir de l'ouverture (3) vers le fond des rainures (6)- un angle d'inclinaison, (αo) par rapport au sens radial avec une composante circonférentielle opposée au sens de déplacement (D) des extrémités des aubes (8), en ce que les axes médians (Mi) des sections transversales de rainures présentent, au niveau des extrémités de rainures situées en aval -à partir de l'ouverture (3) vers le fond des rainures (6)- un angle d'inclinaison (αi) par rapport au sens radial avec une composante circonférentielle dans le sens de déplacement (D) des extrémités des aubes (8), en ce que l'angle d'inclinaison (α) des axes médians (M) des sections transversales de rainures varie en continu entre les extrémités de rainures situées en amont et les extrémités de rainures situées en aval dans le sens d'une torsion/d'un gauchissement, et en ce que les lignes d'intersection (S) -imaginaires- des axes médians (M, Mi, Mo) des sections transversales de rainures avec le contour de l'espace annulaire (R) extérieur au côté du carter sont des segments linéaires au moins approximativement axiaux de sorte que les ouvertures (3) des rainures (2) s'étendent axialement de manière identique.
  2. Structure de carter de compresseur selon la revendication 1, caractérisée en ce que, dans la zone axiale centrale des rainures (2), se trouve une nervure annulaire (11) obturant partiellement les ouvertures (3) des rainures (2), dont le diamètre intérieur coïncide avec la diamètre local du contour de l'espace annulaire (R) extérieur.
  3. Structure de carter de compresseur selon la revendication 1 ou 2, caractérisée en ce que les rainures (2) sont fabriquées, par enlèvement de copeaux, par fraisage, en particulier à l'aide d'une fraise à queue ou d'une fraise sphérique, ou sans enlèvement de copeaux, par coulée ou par étincelage.
  4. Structure de carter de compresseur selon l'une quelconque ou plusieurs des revendications 1 à 3, caractérisée en ce que chaque fond de rainure (6) est arrondi ou au moins les jonctions entre les parois latérales et le fond de rainure sont arrondies.
  5. Structure de carter de compresseur selon l'une quelconque ou plusieurs des revendications 1 à 4, caractérisée en ce que la rugosité de surface moyenne Ra dans les rainures (2) est de 1,6 µm.
  6. Structure de carter de compresseur selon l'une quelconque ou plusieurs des revendications 1 à 5, caractérisée en ce que les bords des ouvertures (3) des rainures (2), c'est-à-dire les jonctions avec le contour de l'espace annulaire extérieur (R), ont une configuration à angles vifs.
  7. Structure de carter de compresseur selon l'une quelconque ou plusieurs des revendications 1 à 6, caractérisée en ce que la profondeur de rainure (T) - respectivement calculée entre la ligne d'intersection (S) des axes médians (M, Mi, Mo) des sections transversales de rainures avec le contour de l'espace annulaire extérieur (R) et le centre du fond de rainure (6) - est constante sur la longueur axiale des rainures ou diminue en continu entre la région, de rainure centrale dans le sens axial et l'extrémité de rainure placée en amont et l'extrémité de rainure placée en aval.
EP02013280A 2001-07-18 2002-06-18 Structure de boítier de compresseur Expired - Lifetime EP1277967B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10135003A DE10135003C1 (de) 2001-07-18 2001-07-18 Verdichtergehäusestruktur
DE10135003 2001-07-18

Publications (2)

Publication Number Publication Date
EP1277967A1 EP1277967A1 (fr) 2003-01-22
EP1277967B1 true EP1277967B1 (fr) 2004-04-14

Family

ID=7692258

Family Applications (1)

Application Number Title Priority Date Filing Date
EP02013280A Expired - Lifetime EP1277967B1 (fr) 2001-07-18 2002-06-18 Structure de boítier de compresseur

Country Status (4)

Country Link
US (1) US6742983B2 (fr)
EP (1) EP1277967B1 (fr)
CA (1) CA2392427C (fr)
DE (2) DE10135003C1 (fr)

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US7074006B1 (en) * 2002-10-08 2006-07-11 The United States Of America As Represented By The Administrator Of National Aeronautics And Space Administration Endwall treatment and method for gas turbine
DE10355241A1 (de) 2003-11-26 2005-06-30 Rolls-Royce Deutschland Ltd & Co Kg Strömungsarbeitsmaschine mit Fluidzufuhr
DE10355240A1 (de) 2003-11-26 2005-07-07 Rolls-Royce Deutschland Ltd & Co Kg Strömungsarbeitsmaschine mit Fluidentnahme
DE102004030597A1 (de) 2004-06-24 2006-01-26 Rolls-Royce Deutschland Ltd & Co Kg Strömungsarbeitsmaschine mit Aussenradstrahlerzeugung am Stator
DE102004043036A1 (de) 2004-09-06 2006-03-09 Rolls-Royce Deutschland Ltd & Co Kg Strömungsarbeitsmaschine mit Fluidentnahme
DE102004055439A1 (de) * 2004-11-17 2006-05-24 Rolls-Royce Deutschland Ltd & Co Kg Strömungsarbeitsmaschine mit dynamischer Strömungsbeeinflussung
US20080044273A1 (en) * 2006-08-15 2008-02-21 Syed Arif Khalid Turbomachine with reduced leakage penalties in pressure change and efficiency
US7827245B2 (en) * 2007-03-06 2010-11-02 International Business Machines Corporation Methods and computer program products for securing display of message content
DE102007037924A1 (de) 2007-08-10 2009-02-12 Rolls-Royce Deutschland Ltd & Co Kg Strömungsarbeitsmaschine mit Ringkanalwandausnehmung
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
DE102008037154A1 (de) 2008-08-08 2010-02-11 Rolls-Royce Deutschland Ltd & Co Kg Strömungsarbeitsmaschine
DE102008052401A1 (de) 2008-10-21 2010-04-22 Rolls-Royce Deutschland Ltd & Co Kg Strömungsarbeitsmaschine mit Laufspalteinzug
DE102008052409A1 (de) 2008-10-21 2010-04-22 Rolls-Royce Deutschland Ltd & Co Kg Strömungsarbeitsmaschine mit saugseitennaher Randenergetisierung
FR2940374B1 (fr) * 2008-12-23 2015-02-20 Snecma Carter de compresseur a cavites optimisees.
US8337146B2 (en) * 2009-06-03 2012-12-25 Pratt & Whitney Canada Corp. Rotor casing treatment with recessed baffles
US9181877B2 (en) 2012-09-27 2015-11-10 United Technologies Corporation Seal hook mount structure with overlapped coating
DE102013210167A1 (de) 2013-05-31 2014-12-04 Rolls-Royce Deutschland Ltd & Co Kg Strukturbaugruppe für eine Strömungsmaschine
DE102013210168A1 (de) 2013-05-31 2014-12-04 Rolls-Royce Deutschland Ltd & Co Kg Strukturbaugruppe für eine Strömungsmaschine
DE102013210169A1 (de) 2013-05-31 2014-12-04 Rolls-Royce Deutschland Ltd & Co Kg Strukturbaugruppe für eine Strömungsmaschine
DE102013210171A1 (de) 2013-05-31 2014-12-04 Rolls-Royce Deutschland Ltd & Co Kg Strukturbaugruppe für eine Strömungsmaschine
US10823194B2 (en) 2014-12-01 2020-11-03 General Electric Company Compressor end-wall treatment with multiple flow axes
CN113007138A (zh) * 2021-03-12 2021-06-22 西北工业大学 一种压气机前置组合式机匣设计方法
CN113007139A (zh) * 2021-03-12 2021-06-22 西北工业大学 一种压气机可调控耦合式机匣处理扩稳方法
EP4306806A1 (fr) * 2022-07-15 2024-01-17 RTX Corporation Traitement de carter pour moteurs à turbine à gaz

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Also Published As

Publication number Publication date
US6742983B2 (en) 2004-06-01
US20030026695A1 (en) 2003-02-06
EP1277967A1 (fr) 2003-01-22
CA2392427C (fr) 2010-09-14
CA2392427A1 (fr) 2003-01-18
DE10135003C1 (de) 2002-10-02
DE50200351D1 (de) 2004-05-19

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