EP2839168A1 - Verbessertes gehäuse für turbomaschinen-blisk und turbomaschine mit diesem gehäuse - Google Patents

Verbessertes gehäuse für turbomaschinen-blisk und turbomaschine mit diesem gehäuse

Info

Publication number
EP2839168A1
EP2839168A1 EP13707679.0A EP13707679A EP2839168A1 EP 2839168 A1 EP2839168 A1 EP 2839168A1 EP 13707679 A EP13707679 A EP 13707679A EP 2839168 A1 EP2839168 A1 EP 2839168A1
Authority
EP
European Patent Office
Prior art keywords
cavity
casing
slots
housing
turbomachine
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
EP13707679.0A
Other languages
English (en)
French (fr)
Other versions
EP2839168B1 (de
Inventor
Cédric Morel
Pascal Romano
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
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 SNECMA SAS filed Critical SNECMA SAS
Publication of EP2839168A1 publication Critical patent/EP2839168A1/de
Application granted granted Critical
Publication of EP2839168B1 publication Critical patent/EP2839168B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/667—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by influencing the flow pattern, e.g. suppression of turbulence
    • 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
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • 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
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/663—Sound attenuation
    • 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
    • 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
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/663—Sound attenuation
    • F04D29/665—Sound attenuation by means of resonance chambers or interference
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/611—Coating

Definitions

  • the invention relates to the field of turbomachines for propelling aeronautical vehicles.
  • turbomachines whose crankcase and blower, including a paddle wheel, are designed to minimize the noise generated by the blower, particularly during the take-off and landing phases, and without decreasing aerodynamic performance in cruising.
  • casings have been developed whose internal surface, located opposite the moving blades, is modified in order to reduce the turbulence of the flow and therefore the noise resulting from this turbulence.
  • a paddle wheel casing comprising, on its inner surface, a plurality of circumferential grooves (grooves symmetrical of revolution about the axis of the casing).
  • the surface of the section of these grooves is decreasing from the first groove, located upstream of the housing, to the last groove, located relatively further downstream.
  • a cavity in a housing connects a plurality of slots.
  • the grooves located further downstream of the casing allow only low aerodynamic gains compared to those located upstream.
  • the observed aerodynamic gain is substantially equal to the gain obtained on a casing comprising only three consecutive grooves.
  • the present invention aims to overcome the problems described above, by providing a paddle wheel casing having improved aerodynamic performance over the prior art.
  • the subject of the invention is a casing for a turbomachine blade wheel comprising an inner coating made of an abradable material, as well as a plurality of circumferential slots arranged in said coating, casing further comprising a circumferential cavity formed in the coating of abradable material, said slots opening into said cavity and extending between said cavity and the inner surface of the casing.
  • the invention may further comprise at least one of the following features:
  • the coating of abradable material having a thickness of between 20 and 25 mm, the cavity has in this thickness, a height of between 5 and 10 mm.
  • the cavity extends in the coating of abradable material being shifted upstream relative to the slot located furthest upstream of said casing, the number of slots is between 4 and 8.
  • each slot has, in the thickness of the coating of abradable material, a height of between 10 and 15 mm.
  • each slot has a width of between 2 and 6 mm.
  • the spacing between two consecutive slots is between 0.5 and 3 mm. the slots each extend in a plane forming an angle with the housing axis of between 70 and 110 °.
  • the invention also relates to a turbomachine comprising a paddle wheel and a paddle wheel casing according to one of the preceding claims.
  • turbomachine according to the invention may further comprise at least one of the following characteristics:
  • the housing cavity is located facing the radially outer end of the blades of the wheel being shifted upstream relative to the leading edge of the blades by a distance of between 2 and 10 mm.
  • the slot located furthest upstream in the casing is offset upstream with respect to the leading edge of the vanes by a distance of between 1.5 and 3.5 mm.
  • FIG. 1 is an axial section of a turbomachine comprising a moving blade wheel and a housing according to the invention.
  • FIG. 2 represents the current lines within a cavity arranged in a turbomachine casing.
  • FIG. 1 shows a casing 10 of a turbomachine turbine wheel 1.
  • the impeller 20, located inside the casing 10, is the fan of the turbomachine. It comprises a plurality of blades 21, rotatably mounted about an axis X-X of rotation of the fan.
  • Each blade 21 has a leading edge 22, a trailing edge 23, and a radially outer end 24 facing the inner surface 15 of the housing. This end 24 is thus caused to move at high speed in the vicinity of the inner surface 15 of the fixed housing 10, causing a turbulent air flow at this location, said turbulent air flow being at the origin of noise.
  • the general direction of the air flow in the turbomachine 1 is represented by the arrow F, which is substantially parallel to the axis XX of rotation of the fan 20, and runs from the leading edge towards the trailing edge of every dawn.
  • the upstream and downstream are used to locate elements of the housing, and are taken with respect to the direction of the air flow.
  • the casing 10, mounted fixed around the impeller 20, is a part of revolution about a housing axis which is coincident with the axis XX of rotation of the impeller 20.
  • the axis of rotation XX is in the following also called crankcase axis.
  • the casing 10 comprises an inner liner 1 1 of an abradable material, the surface of the lining defining the inner surface 15 of the casing 10.
  • This lining has a thickness h- ⁇ , measured radially with respect to the axis of rotation XX, between 20 and 25 mm.
  • slots 12 are circumferential, that is to say they are section circular in an orthogonal plane P to the axis XX of the housing, and go around the housing in this plane.
  • the coating 1 1 abradable material is also arranged a circumferential cavity 13, circular around the slots 12, so that the slots 12 extend between the cavity 13 and the inner surface 15 of the casing 10.
  • the cavity 13 is also opposite the radially outer end 24 of the vanes 21.
  • the slots 12 open into the cavity 13, thus allowing a portion of the air flow F to penetrate inside the cavity 13 by certain slots, and spring in other slots.
  • all the slots 12 open into the cavity 13.
  • the gaps 14 between the slots 12 are formed of the same material 1 1 as the coating of abradable material 1 1. They can be connected to each other and to said coating 1 1 by bridges (not shown in the figures) to ensure the maintenance of the 'together.
  • FIG. 2 shows the current lines of the air flow at the level of the cavity 13. These current lines highlight the role of the slots located upstream in the casing, with respect to the air flow, which sample the vortices linked to the clearance between the blades 21 and the casing 10, and the boundary layer of the flow, both elements being aerodynamically harmful.
  • the current lines also show that the slots located downstream of the casing 10 with respect to the air flow serve to recirculate the flow of air in a less turbulent manner within the flow in the blower 20.
  • the cavity 13 makes it possible to increase the aerodynamic gain of each slot, particularly by conferring on the slots further downstream a specific role, that of the reinjection of the flow into the flow of the fan.
  • This aerodynamic gain is accompanied by a reduction in the noise generated by the turbulent flow.
  • the parameters of the slots 12 and of the cavity 13 have been adapted for an optimization of the aerodynamic gain.
  • the cavity 13 has, in the thickness of the coating 1 1 abradable material, a height h 2 , measured radially relative to the axis XX.
  • Slots 12 in turn, have, in the thickness of the coating 1 1 of abradable material, a height h 3 , measured radially relative to the axis X-X.
  • the slots and the cavity are arranged in the coating of abradable material 1 1, their cumulative height h 2 + h 3 must be less than the thickness h- ⁇ said coating 1 1.
  • the cumulative height of the slots and the cavity must be less than or equal to 15 to 20 mm.
  • the height h 2 of the cavity 13 is between 5 and 10 mm.
  • a cavity whose volume is high allows a larger vortex removal but degrades the recirculation of the flow in the blower 20. Therefore, we must find a compromise on the volume of the cavity, and therefore on its height.
  • this compromise is reached for a height h 2 of the order of 6 mm.
  • the height h 3 of the slots 12 is preferably between 10 and 15 mm, and preferably of the order of 12 mm.
  • the cavity 13 is offset upstream with respect to the first slot 12, which is situated furthest upstream in the casing 10.
  • the cavity 13 must not be flush with at the slot 12 upstream, the upstream end of the cavity must not be in line with this slot 12, because in this case the current lines of this slot would bifurcate abruptly into the cavity, generating a chaotic circulation within this cavity.
  • the cavity 13 has an offset of between 2 and 5 mm, with respect to the upstream end of the first slot 12.
  • the cavity 13 may furthermore have an offset from the last slot 12, which is the slot located furthest downstream in the casing 10.
  • a high number of slots (typically greater than 4) allows an increase in the sampling of vortices, then a better feedback of the flow taken from the air flow in the blower 20.
  • a number of slots exceeding 8 causes an overpressure phenomenon during the reinjection of the flow in the blower, which degrades the aerodynamic performance.
  • a double arrow I the width of a slot 12.
  • the width I is preferably the same for all the slots 12, and is between 2 and 6 mm. For example, this width I is equal to 3.5 mm.
  • the width of an interval 14, ie the spacing between two consecutive slots is represented by a double arrow. This spacing is preferably constant for all intervals 14, and between 0.5 mm and 3 mm.
  • the spacing may be equal to 1 .5 mm.
  • the slots 12 preferably extend, but not limitatively, in a plane forming an angle between 70 ° and 1 10 ° relative to the axis of the housing.
  • the slots extend in a plane orthogonal to said axis.
  • FIG. 1 shows the plane P orthogonal to the axis of the casing and the angle ⁇ formed between the plane P and the axis.
  • the parameters relating to the slots which are the height h 3 , the width I, the spacing entre between two consecutive slots, and the angle ⁇ of slots, are chosen to ensure a good sampling of the vortices in the air flow of the blowing and good circulation of the fluid within the cavity 13.
  • the slot 12 located furthest upstream in the casing 10 is preferably offset upstream with respect to the leading edge 22 of the impeller vanes. a distance ⁇ of between 1.5 and 3.5 mm, this distance being taken between the middle of the slot in the direction of the axis XX and the leading edge 22 of the blade 21. This offset allows better sampling vortices generated by the end 24 of the blade 21.
  • the offset D represented in FIG. 1, between the upstream end of the cavity in the direction of the axis XX, and the leading edge 22 of the blade 21, is preferably between 2 and 10 mm, and advantageously equal to 6 mm.
  • the presence of the cavity 13, also called re-circulating cavity, provides an improvement in aerodynamic and acoustic, by decreasing the turbulent intensity of the air flow near the inner surface of the housing.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP13707679.0A 2012-03-15 2013-03-07 Verbessertes gehäuse für turbomaschinen-blisk und turbomaschine mit diesem gehäuse Active EP2839168B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1252366A FR2988146B1 (fr) 2012-03-15 2012-03-15 Carter pour roue a aubes de turbomachine ameliore et turbomachine equipee dudit carter
PCT/EP2013/054636 WO2013135561A1 (fr) 2012-03-15 2013-03-07 Carter pour roue a aubes de turbomachine ameliore et turbomachine equipee dudit carter

Publications (2)

Publication Number Publication Date
EP2839168A1 true EP2839168A1 (de) 2015-02-25
EP2839168B1 EP2839168B1 (de) 2020-09-23

Family

ID=47827249

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13707679.0A Active EP2839168B1 (de) 2012-03-15 2013-03-07 Verbessertes gehäuse für turbomaschinen-blisk und turbomaschine mit diesem gehäuse

Country Status (9)

Country Link
US (1) US9651060B2 (de)
EP (1) EP2839168B1 (de)
JP (1) JP6170513B2 (de)
CN (1) CN104169589B (de)
BR (1) BR112014022674B1 (de)
CA (1) CA2867058C (de)
FR (1) FR2988146B1 (de)
RU (1) RU2618371C2 (de)
WO (1) WO2013135561A1 (de)

Families Citing this family (8)

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FR2988146B1 (fr) * 2012-03-15 2014-04-11 Snecma Carter pour roue a aubes de turbomachine ameliore et turbomachine equipee dudit carter
RU2645100C1 (ru) * 2016-09-28 2018-02-15 ФЕДЕРАЛЬНОЕ ГОСУДАРСТВЕННОЕ БЮДЖЕТНОЕ ОБРАЗОВАТЕЛЬНОЕ УЧРЕЖДЕНИЕ ВЫСШЕГО ОБРАЗОВАНИЯ "Брянский государственный технический университет" Периферийное устройство для снижения утечек теплоносителя
US12018621B1 (en) 2023-08-16 2024-06-25 Rolls-Royce North American Technologies Inc. Adjustable depth tip treatment with rotatable ring with pockets for a fan of a gas turbine engine
US12078070B1 (en) 2023-08-16 2024-09-03 Rolls-Royce North American Technologies Inc. Adjustable air flow plenum with sliding doors for a fan of a gas turbine engine
US11965528B1 (en) 2023-08-16 2024-04-23 Rolls-Royce North American Technologies Inc. Adjustable air flow plenum with circumferential movable closure for a fan of a gas turbine engine
US12066035B1 (en) 2023-08-16 2024-08-20 Rolls-Royce North American Technologies Inc. Adjustable depth tip treatment with axial member with pockets for a fan of a gas turbine engine
US11970985B1 (en) 2023-08-16 2024-04-30 Rolls-Royce North American Technologies Inc. Adjustable air flow plenum with pivoting vanes for a fan of a gas turbine engine
US12085021B1 (en) 2023-08-16 2024-09-10 Rolls-Royce North American Technologies Inc. Adjustable air flow plenum with movable closure for a fan of a gas turbine engine

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Also Published As

Publication number Publication date
JP6170513B2 (ja) 2017-07-26
CA2867058A1 (en) 2013-09-19
US20150037142A1 (en) 2015-02-05
EP2839168B1 (de) 2020-09-23
BR112014022674A2 (pt) 2017-06-20
FR2988146A1 (fr) 2013-09-20
JP2015510084A (ja) 2015-04-02
CA2867058C (en) 2020-09-22
US9651060B2 (en) 2017-05-16
WO2013135561A1 (fr) 2013-09-19
CN104169589B (zh) 2017-06-23
BR112014022674B1 (pt) 2021-11-30
RU2618371C2 (ru) 2017-05-03
FR2988146B1 (fr) 2014-04-11
CN104169589A (zh) 2014-11-26
RU2014141501A (ru) 2016-05-10

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