EP2268926B1 - Gehäuse für ein sich bewegendes laufrad einer turbomaschine - Google Patents

Gehäuse für ein sich bewegendes laufrad einer turbomaschine Download PDF

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Publication number
EP2268926B1
EP2268926B1 EP09730900A EP09730900A EP2268926B1 EP 2268926 B1 EP2268926 B1 EP 2268926B1 EP 09730900 A EP09730900 A EP 09730900A EP 09730900 A EP09730900 A EP 09730900A EP 2268926 B1 EP2268926 B1 EP 2268926B1
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EP
European Patent Office
Prior art keywords
grooves
casing
downstream
upstream
circumferential grooves
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
EP09730900A
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English (en)
French (fr)
Other versions
EP2268926A2 (de
Inventor
Olivier Domercq
Laurent Jablonski
Vincent Perrot
Antoine Brunet
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 EP2268926A2 publication Critical patent/EP2268926A2/de
Application granted granted Critical
Publication of EP2268926B1 publication Critical patent/EP2268926B1/de
Active 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
    • F04D29/40—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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/08—Sealings
    • F04D29/16—Sealings between pressure and suction sides
    • F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
    • F04D29/164—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of an axial flow wheel
    • 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

Definitions

  • the invention relates to the field of mobile wheels of turbomachines, including compressor wheels.
  • turbomachines mobile wheels associated with fixed wheels form compressor stages whose function is to compress the fluid passing through them.
  • the design and optimization of a mobile wheel grid (s) that is, a series of one or more moving wheels, for example for a compressor, require taking in particular account two objectives.
  • the first goal is to have an optimal compression performance.
  • This compression efficiency can be defined as the ratio of the energy ideally supplied to the fluid for isentropic compression between the upstream and downstream of the moving wheel grid and the energy actually supplied to the fluid. (In this document, the upstream and downstream are defined with respect to the normal flow direction of the fluid through the paddle wheel grid).
  • the second objective is to guarantee a sufficient "pumping margin".
  • Pumping is a phenomenon of fluid instability occurring within a compressor, manifesting itself in low frequency oscillations of the flow, and occurring when the conditions of flow, supply, pressure or temperature move away. the normal operating range of the turbomachine. This unstable phenomenon being generally very energetic, it makes endurance to the turbomachine of strong mechanical stresses (static and dynamic). It is therefore understandable that a permanent objective when developing a mobile wheel grid is to extend as much as possible the normal operating range thereof and, therefore, the compressor or the turbomachine in which it is located, to thus have a sufficient "pumping margin" which makes it possible to avoid pumping phenomena.
  • a crankcase treatment consists for example of making a set of grooves in the inner wall of the housing. With these grooves, the pumping margin of the impeller is improved.
  • the patent GB 24 08 546 thus provides an example of turbomachine casing treatment.
  • the arrangement of the grooves is very particular: it is not about circumferential grooves, but slots circumferentially spaced from each other whose inclination with respect to the radial direction is variable.
  • crankcase treatment in a crankcase according to the preamble of claim 1, is disclosed by the document SU 926,365 .
  • most crankcase treatments are only intended to optimize the pumping margin of the compressor, without worrying about the often negative impact they have on compression performance.
  • the object of the present invention is to define a casing for turbomachine moving blade wheel, said casing having a substantially cylindrical inner wall along a casing axis, this cylindrical wall having a plurality of circumferential grooves, each having a substantially constant section in an axial section plane, and which is optimized to simultaneously improve the pumping margin and optimize the efficiency of the associated turbomachine blade wheel.
  • upstream end is meant above an end of the housing which is provided to be disposed on the upstream side of the housing.
  • circumferential groove is meant grooves which are disposed substantially in a plane perpendicular to the axis of the impeller. These are typically circular grooves drawn in a plane perpendicular to the axis of the impeller. These grooves are not necessarily continuous, and do not necessarily all around the crankcase. However, for them to have sufficient efficiency especially in improving the pumping margin of the mobile wheel grid, it is necessary that they occupy a large part of the circumference of the housing.
  • each circumferential groove has a substantially constant section in an axial section plane means that regardless of the axial sectional plane chosen to evaluate the section, the section of the groove is substantially the same.
  • each of these grooves has a generally negative impact on the compression efficiency of the blade of blades.
  • the surface area of the section of the first groove or grooves is preferred over the following grooves (this is that is, a group of grooves located upstream of the other groove or grooves further downstream).
  • the invention also relates to an embodiment in which the housing has from upstream to downstream, two grooves of sections of the same surface, then two grooves of smaller surface sections and so on.
  • the surface of the section of said circumferential grooves is decreasing from upstream to downstream, from the first to the last groove. This decrease can be regular, for example, when the surface area of the downstream groove section is linear. In another embodiment, the decrease of the groove section surface can also be done in steps.
  • grooves to be considered are the grooves arranged substantially facing the blades of the impeller, regardless of the shape of the casing upstream and downstream of the impeller.
  • the grooves each extend substantially in a plane perpendicular to the axis of the housing.
  • the depth of the first of said circumferential grooves is greater than that of the following grooves further downstream.
  • the depth of said circumferential grooves is decreasing from upstream to downstream.
  • the depth decrease of said circumferential grooves is linear.
  • the width of the first of said circumferential grooves is greater than that of the following grooves located further downstream.
  • the width of said circumferential grooves is decreasing from upstream to downstream along the axis of the housing.
  • the housing has between consecutive grooves substantially cylindrical joining surfaces, and the diameter of the joining surfaces is substantially equal to the average value of the inner diameters of the housing measured respectively upstream and downstream of the grooves.
  • a second object of the invention is to define a turbomachine of high efficiency and whose pumping margin is important.
  • turbomachine comprises a moving impeller, and a casing as defined above.
  • the performance of the turbomachine is optimized, and it enjoys an optimized performance with an improved pumping margin.
  • the figure 1 represents a paddle wheel 100.
  • This paddle wheel 100 consists mainly of a rotor consisting of a rotor disc 30 and blades 20, rotatable along an axis F inside a stator constituted by a housing 10 fixed.
  • the rotor disc 30 is a ring-shaped piece whose function is to hold and rotate the blades 20.
  • the blades are generally attached to the rotor disc by their feet using fasteners said brace or hammer.
  • Each of the blades is thus constituted by a foot, a platform 22 which constitutes the inner part of the flow passage section, and an aerodynamic profile 23.
  • the blades may also be made in the same block of material that the disk rotor, we speak in these cases there blisk monobloc.
  • the flow flows substantially along the axis of F of the impeller, in the inter-blade passages disposed between the aerodynamic profiles 23 of the different blades.
  • the passage of the flow is between the platforms 22 of the blades and inside the casing 10 of the impeller.
  • Each blade has an aerodynamic profile 23 disposed in a substantially radial direction.
  • the foot of the blade is disposed towards the center of the impeller, while the profile 23 extends outwards.
  • the end of the profile 23, during the rotation of the impeller is thus caused to move at high speed in the vicinity of the fixed housing 10.
  • control of the game (B1 B2) between the end of the blade and the inner wall 15 of the housing is important. It is therefore essential that this game be reduced. This game will be detailed in relation to the figure 2 .
  • the figure 2 is a section showing the end of a blade 20 facing the corresponding section of the housing 10.
  • a game is arranged between the blade and the housing . It thus takes a value B1 upstream of the blade and a value B2 downstream in the example shown.
  • the section shows the sections of three grooves 11, 12 and 13 radial or substantially radial. These three grooves are arranged facing the end of the blade 20; they may extend partially upstream or downstream of this end.
  • These grooves 11, 12 and 13 constitute a crankcase treatment whose objective is to improve the margin of pumping in the turbomachine of which the impeller is part, while having an optimal performance of the impeller.
  • the arrangement of grooves according to the invention reveals grooves 11, 12, 13 whose respective sectional surfaces S1, S2, S3 are decreasing from upstream to downstream.
  • the grooves 11, 12 and 13 are radial circular grooves which go around the housing in a plane perpendicular to the axis F thereof.
  • the surfaces S1, S2, S3 decrease linearly. This decrease in the area of the grooves from upstream to downstream and the pre-eminence of the first groove with respect to the following are obtained by varying both the width of the grooves but also their depth.
  • the first groove has the largest width D1 measured along the axis F of the housing, but also the largest depth E1 measured radially.
  • the groove depths decrease, linearly, from upstream to downstream between the three grooves 11, 12, 13 and thus have depths E1, E2, E3 linearly decreasing; similarly, the widths measured along the axis F of the housing D1, D2 and D3 respectively of the three grooves are linearly decreasing from upstream to downstream.
  • the clearances between the end of the vane and the inner wall of the casing 10 vary continuously between upstream and downstream. downstream of the impeller.
  • these games are, from upstream to downstream, a first set B1 to the inner wall 15 of the casing, a set C1 to the joining surface 16 between the grooves 11 and 12, a clearance C2 to the junction surface 17 between the grooves 12 and 13, and finally a clearance B2 to the inner wall 15 of the housing (The concept of play is not defined in the right grooves 11, 12 and 13).
  • the games B1, C1, C2, and B2 have similar values.
  • the junction surfaces 16 and 17 between grooves are substantially cylindrical and have diameters substantially equal to a mean diameter between the upstream diameter A1 measured upstream of the blade 20 and the diameter A2 measured downstream. of it.
  • the grooves 11, 12, 13 shown on the figure 2 extend radially, that is to say each substantially in a plane perpendicular to the axis of the housing. According to one variant, these grooves may also be oblique, that is to say the grooves are not hollowed perpendicularly to the inner wall of the casing, but obliquely, either upstream or downstream of the casing. paddle wheel.
  • the depth E1 of the grooves typically varies from half of the average clearance up to thirty times this, the average clearance being measured between the end of the blade 20 and the inner wall 15 of the housing 10.
  • typically the depth, area and / or groove width is divided by two to five, between the first groove upstream of the crankcase treatment and the last groove of the crankcase treatment.
  • the embodiment presented on the figure 2 has three grooves, whose sections have regularly decreasing surfaces. Many other embodiments can be used. In particular, instead of having these sections of surfaces regularly decreasing, one can have a first group of grooves upstream, all having the same area of section, which would be greater than that common to other grooves further downstream.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Supercharger (AREA)
  • Centrifugal Separators (AREA)

Claims (10)

  1. Gehäuse (10) für ein Laufrad (100) einer Turbomaschine, wobei das Gehäuse eine um eine Gehäuseachse im wesentlichen zylindrische Innenwand (15) aufweist, wobei diese zylindrische Wand eine Vielzahl von Umfangsnuten (11, 12, 13) aufweist, wobei eine jede einen im wesentlichen konstanten Querschnitt in einer axialen Querschnittsebene aufweist, dadurch gekennzeichnet, daß die Fläche des Querschnitts (S1, S2, S3) der Umfangsnuten (11, 12, 13) von stromaufwärts nach stromabwärts, von der stromaufwärtigen ersten Nut (11) zur stromabwärtigen letzten Nut (13) abnehmend ist.
  2. Gehäuse nach Anspruch 1, wobei die Verringerung der Fläche des Querschnitts (S1, S2, S3) der Nuten von stromaufwärts nach stromabwärts linear ist.
  3. Gehäuse nach Anspruch 1 oder 2, wobei die Tiefe (E1) der ersten der Umfangsnuten größer als diejenigen (E2, E3) der folgenden, weiter stromabwärts gelegenen Nuten (12, 13) ist.
  4. Gehäuse nach einem der Ansprüche 1 bis 3, wobei die Tiefe (E1, E2, E3) der Umfangsnuten von stromaufwärts nach stromabwärts abnehmend ist.
  5. Gehäuse nach Anspruch 4, wobei die Abnahme der Tiefe der Umfangsnuten linear ist.
  6. Gehäuse nach einem der Ansprüche 1 bis 5, wobei die Breite (D1) der ersten (11) der Umfangsnuten größer als die (D2, D3) der folgenden, weiter stromabwärts gelegenen Nuten ist.
  7. Gehäuse nach einem der Ansprüche 1 bis 6, wobei die Breite (D1, D2, D3) der Umfangsnuten von stromaufwärts nach stromabwärts abnehmend ist.
  8. Gehäuse nach einem der Ansprüche 1 bis 7, das zwischen aufeinanderfolgenden Nuten im wesentlichen zylindrische Verbindungsflächen (16, 17) aufweist, wobei der Durchmesser der Verbindungsflächen im wesentlichen gleich dem durchschnittlichen Wert der vor bzw. nach den Nuten gemessenen Innendurchmesser (B1, B2) des Gehäuses (10) ist.
  9. Gehäuse nach einem der Ansprüche 1 bis 8, wobei die Nuten (11, 12, 13) sich jeweils im wesentlichen in einer zur Achse (F) des Gehäuses senkrechten Ebene erstrecken.
  10. Turbomaschine, die ein Laufrad (100) und ein Gehäuse nach einem der Ansprüche 1 bis 9 umfaßt.
EP09730900A 2008-03-28 2009-03-25 Gehäuse für ein sich bewegendes laufrad einer turbomaschine Active EP2268926B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0852012A FR2929349B1 (fr) 2008-03-28 2008-03-28 Carter pour roue a aubes mobiles de turbomachine
PCT/FR2009/050516 WO2009125135A2 (fr) 2008-03-28 2009-03-25 Carter pour roue a aubes mobiles de turbomachine

Publications (2)

Publication Number Publication Date
EP2268926A2 EP2268926A2 (de) 2011-01-05
EP2268926B1 true EP2268926B1 (de) 2011-08-24

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EP09730900A Active EP2268926B1 (de) 2008-03-28 2009-03-25 Gehäuse für ein sich bewegendes laufrad einer turbomaschine

Country Status (11)

Country Link
US (1) US8777558B2 (de)
EP (1) EP2268926B1 (de)
JP (1) JP5575741B2 (de)
CN (1) CN102016324B (de)
AT (1) ATE521812T1 (de)
BR (1) BRPI0910320B1 (de)
CA (1) CA2718847C (de)
ES (1) ES2372266T3 (de)
FR (1) FR2929349B1 (de)
RU (1) RU2491447C2 (de)
WO (1) WO2009125135A2 (de)

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CN105298923A (zh) * 2014-06-17 2016-02-03 中国科学院工程热物理研究所 压气机前缝后槽式机匣处理扩稳装置

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GB2483060B (en) * 2010-08-23 2013-05-15 Rolls Royce Plc A turbomachine casing assembly
GB2487900B (en) * 2011-02-03 2013-02-06 Rolls Royce Plc A turbomachine comprising an annular casing and a bladed rotor
FR2988146B1 (fr) 2012-03-15 2014-04-11 Snecma Carter pour roue a aubes de turbomachine ameliore et turbomachine equipee dudit carter
WO2014158236A1 (en) * 2013-03-12 2014-10-02 United Technologies Corporation Cantilever stator with vortex initiation feature
CN106030039A (zh) * 2014-02-25 2016-10-12 西门子公司 具有深度变化材料性质的涡轮机部件热障涂层
US10465716B2 (en) 2014-08-08 2019-11-05 Pratt & Whitney Canada Corp. Compressor casing
GB201415201D0 (en) * 2014-08-28 2014-10-15 Rolls Royce Plc A wear monitor for a gas turbine engine fan
US20160153465A1 (en) * 2014-12-01 2016-06-02 General Electric Company Axial compressor endwall treatment for controlling leakage flow therein
US10047620B2 (en) * 2014-12-16 2018-08-14 General Electric Company Circumferentially varying axial compressor endwall treatment for controlling leakage flow therein
US10066640B2 (en) * 2015-02-10 2018-09-04 United Technologies Corporation Optimized circumferential groove casing treatment for axial compressors
US10107307B2 (en) 2015-04-14 2018-10-23 Pratt & Whitney Canada Corp. Gas turbine engine rotor casing treatment
US10844868B2 (en) 2015-04-15 2020-11-24 Robert Bosch Gmbh Free-tipped axial fan assembly
US10487847B2 (en) 2016-01-19 2019-11-26 Pratt & Whitney Canada Corp. Gas turbine engine blade casing
KR102199473B1 (ko) * 2016-01-19 2021-01-06 한화에어로스페이스 주식회사 유체 이송 장치
US10428674B2 (en) * 2017-01-31 2019-10-01 Rolls-Royce North American Technologies Inc. Gas turbine engine features for tip clearance inspection
US10648484B2 (en) * 2017-02-14 2020-05-12 Honeywell International Inc. Grooved shroud casing treatment for high pressure compressor in a turbine engine
US10914318B2 (en) * 2019-01-10 2021-02-09 General Electric Company Engine casing treatment for reducing circumferentially variable distortion
CN112283167B (zh) * 2020-11-20 2022-04-01 西安热工研究院有限公司 一种用于轴流压气机的周向槽类机匣处理设计方法
FR3125316A1 (fr) * 2021-07-16 2023-01-20 Safran Aircraft Engines Element abradable comportant un temoin d'usure
US20230151825A1 (en) * 2021-11-17 2023-05-18 Pratt & Whitney Canada Corp. Compressor shroud with swept grooves
CN114658689A (zh) * 2022-03-17 2022-06-24 哈尔滨工业大学 蜗壳和离心压气机

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Publication number Priority date Publication date Assignee Title
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CN105298923B (zh) * 2014-06-17 2018-01-02 中国科学院工程热物理研究所 压气机前缝后槽式机匣处理扩稳装置

Also Published As

Publication number Publication date
CN102016324A (zh) 2011-04-13
FR2929349B1 (fr) 2010-04-16
JP5575741B2 (ja) 2014-08-20
CA2718847A1 (fr) 2009-10-15
RU2491447C2 (ru) 2013-08-27
CA2718847C (fr) 2016-01-05
ATE521812T1 (de) 2011-09-15
ES2372266T3 (es) 2012-01-17
BRPI0910320A2 (pt) 2015-09-29
CN102016324B (zh) 2014-04-16
US20110085896A1 (en) 2011-04-14
JP2011515622A (ja) 2011-05-19
WO2009125135A2 (fr) 2009-10-15
EP2268926A2 (de) 2011-01-05
US8777558B2 (en) 2014-07-15
BRPI0910320B1 (pt) 2020-02-18
RU2010144039A (ru) 2012-05-10
FR2929349A1 (fr) 2009-10-02
WO2009125135A3 (fr) 2009-12-10

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