EP3574219A1 - Pale de rouet pour turbomachine, comprenant une ailerette a son sommet et au bord d'attaque - Google Patents
Pale de rouet pour turbomachine, comprenant une ailerette a son sommet et au bord d'attaqueInfo
- Publication number
- EP3574219A1 EP3574219A1 EP18702788.3A EP18702788A EP3574219A1 EP 3574219 A1 EP3574219 A1 EP 3574219A1 EP 18702788 A EP18702788 A EP 18702788A EP 3574219 A1 EP3574219 A1 EP 3574219A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- blade
- fin
- skeleton
- turbomachine
- leading edge
- 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.)
- Withdrawn
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
- F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
- F04D17/06—Helico-centrifugal pumps
-
- 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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/04—Blade-carrying members, e.g. rotors for radial-flow machines or engines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
- F04D17/08—Centrifugal pumps
- F04D17/10—Centrifugal pumps for compressing or evacuating
-
- 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
- F04D29/26—Rotors specially for elastic fluids
- F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
- F04D29/30—Vanes
-
- 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
-
- 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
- F05D2220/00—Application
- F05D2220/40—Application in turbochargers
Definitions
- the invention relates to the general technical field of aircraft turbomachines, such as turbine engines. More specifically, the invention relates to centrifugal and / or diagonal compressor wheels for a turbomachine.
- a turbo-propeller centrifugal compressor wheel of known structure comprises a carrier and a plurality of blades which are connected to the carrier.
- Each of the blades extends from one foot towards a vertex in the direction of the height of the blade, and from a leading edge to a trailing edge in the direction of the skeleton of the blade.
- the blade includes an aerodynamic wall that connects the leading edge to the trailing edge.
- the blades can take various forms.
- Some blades of the wheel are said interleaves. They are shorter in the direction of the skeleton than other so-called main blades and they aim to increase the aerodynamic performance of the compressor.
- the invention aims to at least partially solve the problems encountered in the solutions of the prior art.
- the invention relates to a rotor blade for a turbomachine compressor.
- the blade includes a foot and a vertex spaced from each other in a direction of the height of the blade.
- the blade comprises a body extending between the foot and the top in the direction of height, and extending from a leading edge to a trailing edge in a direction of the skeleton of the blade.
- the body has a curvature oriented in a first direction of rotation relative to the direction of the skeleton.
- the blade comprises a fin located in the extension of the body in the direction of height, the top of the blade and the leading edge of the blade.
- the fin has a curvature in a second direction of rotation opposite the first direction of rotation.
- the blade according to the invention limits the marginal vortices in the compressor and thus increases its efficiency. In particular, it limits the flow disturbances due to the clearance between the blades and the compressor housing.
- the invention may optionally include one or more of the following features combined with one another or not.
- the fin is initiated at the leading edge and extending towards the trailing edge.
- the length of the fin in the direction of the skeleton is between 0% and 100% of the length of the blade in the direction of the skeleton.
- the width of the fin in the transverse direction of the blade decreases progressively from the leading edge to the trailing edge.
- the height of the fin is between 50% and 100% of the height of the blade.
- the distal end of the flange forms an angle of between 90 ° and 180 ° with the body, according to at least one cutting plane of the body which is substantially orthogonal to the direction of the skeleton.
- the fin has a concave shape according to at least one cutting plane of the body which is substantially orthogonal to the direction of the skeleton.
- the fin has a wall shape twisted relative to the body about a twisting axis which is shifted transversely to a center line of the blade in the direction of the skeleton.
- the invention also relates to a rotor for a turbomachine compressor comprising a blade as defined above.
- the wheel comprises the main pa and intermediate blades interposed between the main blades, at least one of the intermediate blades being a blade as defined above.
- the body comprises an underside face and an extrados face opposite to the underside face in a transverse direction of the blade, the fin being oriented towards an extrados face of a main blade adjacent to the intermediate blade and vis-à-vis which is located the intrados face of the intermediate blade.
- the invention also relates to a centrifugal and / or diagonal compressor for a turbomachine comprising a wheel as defined above.
- Diagonal compressors are also known as mixed compressors. These types of compressors have an intermediate output between an axial output of an axial compressor and a radial output of a centrifugal compressor.
- turbomachine comprising a compressor as defined above.
- the turbomachine is preferably an aircraft turbine engine, such as a turbine engine for a helicopter.
- Figure 1 is a schematic representation partially in longitudinal section of a helicopter turbine engine, according to a first embodiment of the invention
- FIG. 2 is a partial schematic perspective view of the centrifugal compressor wheel of the turbine engine according to the first embodiment
- FIG. 3 is a partial schematic representation in perspective of an intermediate blade of the impeller of the turbine engine according to the first embodiment.
- Figure 1 shows a turbine engine 1 helicopter.
- the turbine engine 1 is substantially symmetrical in revolution about an axial direction X-X of the turbine engine.
- the turbine engine 1 comprises a compressor 2 of centrifugal type which comprises a wheel 10.
- the turbine engine 1 comprises from upstream to downstream a diffuser 3, a combustion chamber 4, a high-pressure turbine 5 and a free turbine 6.
- the compressor 2, the high-pressure turbine 5 are mounted on a shaft 23 which extends substantially in the axial direction XX.
- the free turbine 6 is mounted on a shaft coaxial with the shaft 23.
- a radial direction is a direction substantially orthogonal to the axis of the turbine engine X-X and intersecting this axis.
- the turbine engine 1 has an air inlet 7, the air passing through this inlet 7 to reach the compressor 2.
- the rotation of the wheel 10 about its axis of rotation XX sucks the air upstream of the wheel 10 and the speed of the fluid passing through the wheel 10 is progressively transformed into a radial velocity, the fluid exiting at the outer periphery of the wheel 10.
- the air enters the wheel 10 in a direction rather parallel to the axis of rotation XX of the wheel, shown in the section of Figure 1 by the arrows Fl, and out of the wheel 10 in a radial direction perpendicular to the axis A, represented by arrows F2.
- the air coming out of the impeller 10 passes through the diffuser 3 before reaching the combustion chamber 4.
- the combustion gases leaving the chamber 4 rotate the high-pressure turbine 5 and the free turbine 6, which in turn drive the combustion engine shaft 23 of the compressor 2 in rotation about its axis XX, as well as the coaxial shaft on which the free turbine 6 is mounted.
- This compressor 2 comprises the centrifugal wheel 10 and a housing 21 which surrounds externally the blades 30, 40 of the wheel 10.
- the wheel 10 comprises a flared support 13 and blades 30, 40 which are rigidly secured to the support 13.
- the support 13 flares downstream, extending radially from a hub 11 until at a circumferential edge 15.
- the downstream portion of the impeller 10 is closed by a radial flange which is rigidly secured to the support 13.
- the blades 30, 40 of the impeller each extend from upstream to downstream from a leading edge BA to a trailing edge BF in a direction of the skeleton S-S of the blade.
- This direction of the S-S skeleton is curvilinear and corresponds to the median line of the blade in the transverse direction Z-Z of the blade, which connects the leading edge BA to the trailing edge BF.
- the trailing edge BF of the blades is located near the circumferential edge 15 with respect to the axis of rotation X-X.
- Each blade 30, 40 also extends in the direction of its height Y-
- the blades 30, 40 comprise main blades 30 and intermediate blades 40 which are interposed between the main blades 30 about the axis of rotation X-X of the compressor.
- the main blades 30 have a longer length in the direction of the S-S skeleton than the spacer blades 40.
- the leading edge BA of the main blades 30 is situated further upstream than that of the intermediate blades 40.
- Each main blade 30 comprises a single wall which has a lower face 31 and an extrados face 35 opposite to the intrados face according to a transverse direction of the blade.
- the intrados face 31 and the extrados face 35 each connect the leading edge BA of the blade to its trailing edge BF.
- the main blades 30 are twisted.
- Each intermediate blade 40 also includes an extrados face 45 and a lower face 46 which each connect the leading edge BA of the blade to its trailing edge BF.
- the extrados face 45 of each intermediate blade 40 is opposite the lower surface face 31 of one of the adjacent main blades 30.
- the intrados face 46 of each intermediate blade is opposite the extrados face 35 of one of the adjacent main blades 30.
- each intermediate blade 40 comprises a body 41 which extends from the foot P of this blade towards the top S of the blade, as well as a fin 50 which is located in the extension of the body in the direction of the height YY and which includes the vertex S of the blade.
- the body 41 corresponds to a lower aerodynamic portion of the blade 40.
- the fin 50 corresponds to an upper aerodynamic portion of the blade 40.
- the body 41 extends from the leading edge BA of the blade to its trailing edge BF in the direction of the S-S skeleton.
- the fin 50 is initiated at the leading edge BA of the blade and extends towards the trailing edge BF in the direction of the S-S skeleton.
- the transverse direction Z-Z is a direction orthogonal to the direction of the S-S skeleton and to the direction of the Y-Y height of the blade. It corresponds to the direction of the width of the blade 40.
- the body 41 has, at the level of the extrados face 45, a generally twisted shape with a non-zero curvature in a first direction which is oriented opposite the intrados face 46 in the transverse direction Z-Z.
- the fin 50 has a curved shape relative to the body 41. Its curvature is greater than that of the body.
- the fin 50 has a curvature oriented towards the intrados face 46 of the blade in the transverse direction ZZ. It has a curvature da ns a second direction opposite to the first direction, that is to say in a direction opposite to that of the curvature of the extrados face 45 at the level of the body 41.
- the fin 50 has a twisted portion of the wall portion relative to the body
- It has a concave shape according to at least one cutting plane of the body 41 which is substantially orthogonal to the direction of the S-S skeleton.
- the distal end of the fin forms an angle ⁇ between 90 ° and 180 ° with the body 41 in this plane.
- the length I of the fin 50 in the direction of the S-S skeleton is between 0% and 100% of the length L of the blade 40 in the direction of the S-S skeleton.
- the height h of the fin 50 is between 50% and substantially
- the fin 50 has a width e which decreases in the direction of the S-S skeleton from the leading edge BA towards the trailing edge BF.
- the maximum width e of the fin 50 is between 1% and 30% of the length L of the blade 40.
- the fin 50 limits the marginal vortices in the compressor 2, especially at the top of the blade S, thereby increasing the isentropic efficiency of the compressor 2.
- the spacer blades 40 limit the gas flow disturbances in the compressor 2 due to the clearance between the blades 30, 40 and the housing 21 of the compressor.
- the overall shape, the dimensions and the curvature of the fin 50 may vary with respect to that shown in FIGS. 2 and 3.
- at least some of the main blades 30 may each comprise a fin 50, in addition to or instead of the intermediate blades 40.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1750685A FR3062431B1 (fr) | 2017-01-27 | 2017-01-27 | Pale de rouet pour turbomachine, comprenant une ailerette a son sommet et au bord d'attaque |
PCT/FR2018/050167 WO2018138438A1 (fr) | 2017-01-27 | 2018-01-25 | Pale de rouet pour turbomachine, comprenant une ailerette a son sommet et au bord d'attaque |
Publications (1)
Publication Number | Publication Date |
---|---|
EP3574219A1 true EP3574219A1 (fr) | 2019-12-04 |
Family
ID=58347685
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP18702788.3A Withdrawn EP3574219A1 (fr) | 2017-01-27 | 2018-01-25 | Pale de rouet pour turbomachine, comprenant une ailerette a son sommet et au bord d'attaque |
Country Status (6)
Country | Link |
---|---|
US (1) | US11187234B2 (fr) |
EP (1) | EP3574219A1 (fr) |
CN (1) | CN110234886A (fr) |
CA (1) | CA3051802A1 (fr) |
FR (1) | FR3062431B1 (fr) |
WO (1) | WO2018138438A1 (fr) |
Families Citing this family (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US10221858B2 (en) | 2016-01-08 | 2019-03-05 | Rolls-Royce Corporation | Impeller blade morphology |
CN111664052A (zh) * | 2020-06-24 | 2020-09-15 | 曹正武 | 一种叶梢小翼式螺旋桨(风扇) |
CN113202789B (zh) * | 2021-06-09 | 2022-09-30 | 清华大学 | 离心压缩机用叶轮及离心压缩机 |
CZ2022257A3 (cs) * | 2022-06-10 | 2023-11-22 | ÄŚeskĂ© vysokĂ© uÄŤenĂ technickĂ© v Praze | Lopatka oběžného kola umístěná na kompresorovém kole |
Family Cites Families (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3984193A (en) * | 1974-10-07 | 1976-10-05 | General Motors Corporation | Radial-flow turbomachine |
US5437541A (en) * | 1993-12-30 | 1995-08-01 | Vainrub; John | Blade for axial fan |
US6663347B2 (en) * | 2001-06-06 | 2003-12-16 | Borgwarner, Inc. | Cast titanium compressor wheel |
EP1953344B1 (fr) * | 2007-02-05 | 2012-04-11 | Siemens Aktiengesellschaft | Aube de turbine |
FR2943103B1 (fr) * | 2009-03-13 | 2011-05-27 | Turbomeca | Compresseur axialo-centrifuge a angle de rake evolutif |
DE102009024568A1 (de) * | 2009-06-08 | 2010-12-09 | Man Diesel & Turbo Se | Verdichterlaufrad |
FR2969230B1 (fr) * | 2010-12-15 | 2014-11-21 | Snecma | Aube de compresseur a loi d'empilage amelioree |
US8951009B2 (en) * | 2011-05-23 | 2015-02-10 | Ingersoll Rand Company | Sculpted impeller |
CN202209308U (zh) * | 2011-08-23 | 2012-05-02 | 无锡杰尔压缩机有限公司 | 一种高效的全三元叶轮 |
JP5606515B2 (ja) * | 2012-12-13 | 2014-10-15 | 三菱重工業株式会社 | 圧縮機 |
CN104373376A (zh) * | 2014-10-29 | 2015-02-25 | 湖南天雁机械有限责任公司 | 弧形斜流涡轮增压器压气机叶轮 |
-
2017
- 2017-01-27 FR FR1750685A patent/FR3062431B1/fr active Active
-
2018
- 2018-01-25 WO PCT/FR2018/050167 patent/WO2018138438A1/fr unknown
- 2018-01-25 CN CN201880008848.5A patent/CN110234886A/zh active Pending
- 2018-01-25 CA CA3051802A patent/CA3051802A1/fr active Pending
- 2018-01-25 US US16/480,046 patent/US11187234B2/en active Active
- 2018-01-25 EP EP18702788.3A patent/EP3574219A1/fr not_active Withdrawn
Also Published As
Publication number | Publication date |
---|---|
US11187234B2 (en) | 2021-11-30 |
CA3051802A1 (fr) | 2018-08-02 |
FR3062431A1 (fr) | 2018-08-03 |
CN110234886A (zh) | 2019-09-13 |
WO2018138438A1 (fr) | 2018-08-02 |
US20200003219A1 (en) | 2020-01-02 |
FR3062431B1 (fr) | 2021-01-01 |
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