EP2978977B1 - Ailette pour diffuseur d'un compresseur radial ou mixte - Google Patents
Ailette pour diffuseur d'un compresseur radial ou mixte Download PDFInfo
- Publication number
- EP2978977B1 EP2978977B1 EP14718669.6A EP14718669A EP2978977B1 EP 2978977 B1 EP2978977 B1 EP 2978977B1 EP 14718669 A EP14718669 A EP 14718669A EP 2978977 B1 EP2978977 B1 EP 2978977B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- leading edge
- vane
- trailing edge
- radial
- diffuser
- 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
Links
- 239000007789 gas Substances 0.000 description 16
- 238000009792 diffusion process Methods 0.000 description 7
- 239000012530 fluid Substances 0.000 description 5
- 238000005086 pumping Methods 0.000 description 5
- 230000003068 static effect Effects 0.000 description 5
- 241000251556 Chordata Species 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 238000011144 upstream manufacturing Methods 0.000 description 3
- 241000940835 Pales Species 0.000 description 2
- 206010033546 Pallor Diseases 0.000 description 2
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 230000000903 blocking effect Effects 0.000 description 1
- 238000007664 blowing Methods 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 239000000470 constituent Substances 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
Images
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
- F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
- F04D29/44—Fluid-guiding means, e.g. diffusers
- F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
- F04D29/444—Bladed diffusers
-
- 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
- F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
- F04D29/44—Fluid-guiding means, e.g. diffusers
-
- 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
- F04D17/12—Multi-stage pumps
-
- 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
- F05D2250/00—Geometry
- F05D2250/50—Inlet or outlet
- F05D2250/52—Outlet
Definitions
- the invention relates generally to gas turbine engines, and more particularly to a fin of a diffuser for a radial or mixed compressor, a diffusion stage of a radial or mixed compressor of a gas turbine, and 'to an associated compressor.
- a compressor comprises one or more rotating disks (rotor or wheel), bladed or not and one or more fixed vane wheels (rectifier stages).
- a radial (or centrifugal) compressor has at least one radial compression stage, that is to say capable of producing a flow of gas perpendicular to the central axis of the compressor. It comprises at least one radial impeller which sucks the air axially, which, under the effect of the radial force, is accelerated, compressed and discharged radially. This air is then straightened in a diffuser (fixed blade) which transforms part of its speed into static pressure by slowing the gases at the exit of the wheel. The operation must take place with a minimum of total pressure loss while maintaining a satisfactory compressor stability level in order to maintain an acceptable pumping margin for the operation of the turbomachine.
- the gases are then guided to the combustion chamber.
- a mixed compressor (or helico-radial) has at least one compression stage inclined with respect to said central axis, so that the fluid leaves the compressor impeller at a non-zero angle with the radial direction.
- a diffuser of a radial compressor is composed of a wheel formed of two flanges between which the gases flow radially or inclined from the center to the periphery.
- the fins are distributed between the flanges along the wheel. These fins form a flow grid between the leading edges of these fins and the trailing edges.
- the deflection of the air flow at the exit of the impeller by the fins of the diffuser can cause a detachment of the fluid on the lower surface or the upper surface of the fins, which detachment, as long as it is important, can lead to the stall. fluid and, consequently, pumping. It is known that this pumping phenomenon is harmful to the constituent elements of the compressor, so that we try to avoid it as far as possible.
- the vanes of the diffuser are constructed from a lower surface and an extrados wall in the shape of a circular arc, and comprise a quasi-linear angle law.
- An example of such a fin is illustrated in figure 1 .
- these fins have a limitation in terms of diffusing capacity. Indeed, an increase in the diffusion by these fins causes a drop in isentropic efficiency and an increase in the instability of the compressor.
- S S -shaped fins of similar profile have also been described in the document JP 2011-252424 .
- the fins of this document are configured so that an angle formed between the line of curvature and the circumferential profile increases, then decreases, then increases again between the leading edge and the trailing edge of the fin .
- the section at the neck of the diffuser must be restricted, which has the effect of reducing the stability of the diffuser.
- An object of the invention is to improve the performance and pumping margin of diffusers of radial and mixed compressors of the prior art.
- the invention also proposes a diffuser comprising at least one fin as described above, as well as a radial or mixed compressor comprising such a diffuser, and an engine comprising such a compressor.
- a radial diffuser according to the present invention is particularly intended to be used with a compressor 2 of radial or mixed type.
- the figure 4 is a partial section of a motor 1 comprising a radial compressor 2.
- a gas flow F is first drawn into an air inlet sleeve, then compressed between the blades 3a of a wheel 3 of the radial compressor 2 and its crankcase.
- the compressor 2 is of axial symmetry around an axis X.
- the compressed gas flow F then exits radially from the wheel 3. If the compressor 2 was mixed, the gas flow would exit inclined at a non-zero angle with respect to a radial direction to the X axis.
- the compressed air leaves the wheel 3 radially while having a kinetic moment and passes through a diffuser 5.
- the role of the diffuser 5 is to convert a portion of the kinetic energy of the gas from the compressor 2 in static pressure by slowing the speed of gases, and straighten the flow from the wheel 3. It comprises for this a plurality of fins 10 arranged along its circumference, which extend between a front flange 5a and a rear flange 5b.
- Each of the fins 10 has, in known manner, a leading edge 11 disposed opposite a gas flow, a trailing edge 12 opposite the leading edge 11, an extrados side wall 13 and a side wall intrados 14 which connect the leading edge 11 to the trailing edge 12.
- the front flanges 5a and rear 5b may be planar.
- at least one of the flanges 5a, 5b may comprise, in the space they define between them, at least one zone with alternating curvature between two fins 10, so that the air stream may comprise evolutionary head and foot meridians.
- the flanges 5a, 5b may be evolutionary shapes axisymmetric.
- front flanges 5a and 5b rear can be arranged to allow suction and blowing into the diffuser 5.
- the fin 10 comprises a profile whose camber line 15 has at least two points of inflection I1, I2 between its leading edge 11 and its trailing edge 12, that is to say at least two changes of concavity.
- the inflection points I1, I2 together define the capture zone, which comprises the portion of the fin 10 extending upstream of the first point of inflection I1, of the diffusion zone, which comprises the part of the fin 10 which extends downstream of the second point of inflection I2.
- the points of inflection I1, I2 are situated between 10% and 90% of the cord 16, preferably between 30% and 70%. %.
- a first I1 of the inflection points may be between 35% and 55% of the cord 16, while the second point of inflection I2 is between 55% and 65% of the cord 16.
- the points I1, I2 may in particular be arranged symmetrically with respect to the center of the rope 16.
- the profile of the fin 10 may comprise more points of inflection I1, I2.
- the camber line 15 presents successively at least, between the leading edge 11 and the trailing edge 12, a first concavity, a second concavity different from the first concavity, then a third concavity.
- the inflection points I1, I2 are symmetrical relative to the center of the rope 16, the second concavity is then centered in the fin 10.
- the intrados wall 14 and the extrados wall 13 substantially follow the curvature of the camber line 15, and therefore have as many points of inflection I1, I2.
- the intrados wall 14 and the extrados wall 13 thus comprise two points of inflection I1, I2.
- the intrados wall 14 comprises a convex portion 14a between the leading edge 11 and the first point of inflection, then a concave portion 14b between the two points of inflection I1, I2, and a convex portion 14c between the second inflection point and the trailing edge 12.
- the upper surface 13 as for it comprises a concave portion 13a between the leading edge 11 and the first point of inflection, then a convex portion 13b between the two points d I1, I2, then a concave portion 13c between the second inflection point and the trailing edge 12.
- camber line 15 extends between the intrados wall 14 and the rope 16. In other words, at any point between the leading edge 11 and the trailing edge 12, the line of camber 15 and the intrados wall 14 extend away from the rope 16. In addition, the concave areas of the upper wall 13 pass through the rope 16, and are therefore at least partially on the same side as the line camber 15 of said rope 16.
- the leading edge 11 and the trailing edge 12 are oriented in the same general direction with respect to the flow of the gas that usually encountered in conventional diffusers, which allows to preserve the cross section, that is to say the inlet section of the fluid between two fins 10 adjacent. In this way, the stability of the diffuser 5 is maintained while improving the diffusion of the flow.
- the angle of attack ⁇ (which corresponds to the angle between the tangent to the camber line 15 at the leading edge 11 and the rope 16) may be substantially identical to that of the conventional fins.
- the angle of attack ⁇ can be between about 0 ° and about 45 °. In this way, it is possible to substantially retain the shape of the conventional diffuser fins 5 in their area of capture, thereby preserving the stability of the flow.
- the presence of the second point of inflection I2 makes it possible to modify the shape of the fins 10 in their diffusion zone to increase the efficiency of the diffuser 5, without modifying the shape of the capture zone.
- the camber line 15 of the fin profile 10 comprises at least two points of inflection I1, I2.
- the number of inflection points I1, I2 may be even in order to maintain the general orientation of the leading edge 11 and the trailing edge 12 with respect to the flow, and thus to preserve the neck section.
- the corresponding camber line 15 again extends between the intrados wall 14 and the rope 16, so that at any point between the leading edge 11 and the 12, the camber line 15 and the intrados wall 14 extend at a distance from the rope 16, and the concave zones of the extrados wall 13 pass through the rope 16.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1352829A FR3003908B1 (fr) | 2013-03-28 | 2013-03-28 | Diffuseur a ailettes d un compresseur radial ou mixte |
PCT/FR2014/050693 WO2014154997A1 (fr) | 2013-03-28 | 2014-03-25 | Diffuseur à ailettes d'un compresseur radial ou mixte |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2978977A1 EP2978977A1 (fr) | 2016-02-03 |
EP2978977B1 true EP2978977B1 (fr) | 2016-10-19 |
Family
ID=48901098
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP14718669.6A Active EP2978977B1 (fr) | 2013-03-28 | 2014-03-25 | Ailette pour diffuseur d'un compresseur radial ou mixte |
Country Status (11)
Country | Link |
---|---|
US (1) | US9890792B2 (ko) |
EP (1) | EP2978977B1 (ko) |
JP (1) | JP6367917B2 (ko) |
KR (1) | KR102196815B1 (ko) |
CN (1) | CN105247223B (ko) |
CA (1) | CA2908081C (ko) |
ES (1) | ES2606831T3 (ko) |
FR (1) | FR3003908B1 (ko) |
PL (1) | PL2978977T3 (ko) |
RU (1) | RU2651905C2 (ko) |
WO (1) | WO2014154997A1 (ko) |
Families Citing this family (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE102014221362A1 (de) | 2014-10-21 | 2016-04-21 | Siemens Aktiengesellschaft | Profilierung von Leitschaufeln von Leitapparaten bei Turbomaschinen, insbesondere Verdichtern |
DE102015107907A1 (de) * | 2015-05-20 | 2016-11-24 | Ebm-Papst Mulfingen Gmbh & Co. Kg | Ebenes Strömungsleitgitter |
US9732775B2 (en) * | 2015-06-24 | 2017-08-15 | The Boeing Company | Flow straightener apparatus and systems for ducted air |
KR101848437B1 (ko) * | 2017-03-28 | 2018-04-13 | 한국과학기술연구원 | 신축성 가변형 디퓨저 베인이 구비된 원심형 터보 기계 |
KR102083168B1 (ko) * | 2017-11-07 | 2020-03-02 | 주식회사 에어로네트 | 주 날개 및 보조 날개를 구비한 임펠러 |
KR102427392B1 (ko) * | 2018-01-24 | 2022-07-29 | 한화에어로스페이스 주식회사 | 압축기용 디퓨저 |
US11421708B2 (en) | 2018-03-16 | 2022-08-23 | Carrier Corporation | Refrigeration system mixed-flow compressor |
KR102095835B1 (ko) | 2019-01-25 | 2020-04-01 | (주)대주기계 | 파형 회전실린더를 가지는 산업용 디퓨저 |
US10989219B2 (en) | 2019-02-04 | 2021-04-27 | Honeywell International Inc. | Diffuser assemblies for compression systems |
US11098730B2 (en) * | 2019-04-12 | 2021-08-24 | Rolls-Royce Corporation | Deswirler assembly for a centrifugal compressor |
CN112651117B (zh) * | 2020-12-21 | 2023-03-28 | 贵州电网有限责任公司 | 一种水电机组导叶动态分段关闭方法 |
CN113339267B (zh) * | 2021-06-17 | 2022-07-26 | 清华大学 | 一种弓形高能量密度叶片设计方法及其设计的叶片泵 |
Family Cites Families (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3298636A (en) * | 1965-01-15 | 1967-01-17 | Arnholdt Eric | Airfoil |
SU1409785A2 (ru) * | 1986-12-23 | 1988-07-15 | Университет дружбы народов им.Патриса Лумумбы | Лопаточный диффузор центробежного компрессора |
US5395071A (en) * | 1993-09-09 | 1995-03-07 | Felix; Frederick L. | Airfoil with bicambered surface |
JP3948785B2 (ja) | 1996-05-17 | 2007-07-25 | カルソニックカンセイ株式会社 | 遠心多翼ファン |
FR2937385B1 (fr) * | 2008-10-17 | 2010-12-10 | Turbomeca | Diffuseur muni d'aubes a orifices |
CN101865145B (zh) * | 2009-04-20 | 2012-09-19 | 日立空调·家用电器株式会社 | 电动鼓风机、搭载电动鼓风机的电动吸尘器及其制造方法 |
EP2299124A1 (de) * | 2009-09-04 | 2011-03-23 | Siemens Aktiengesellschaft | Verdichterlaufschaufel für einen Axialverdichter |
FR2958967B1 (fr) * | 2010-04-14 | 2013-03-15 | Turbomeca | Procede d'adaptation de debit d'air de turbomachine a compresseur centrifuge et diffuseur de mise en oeuvre |
JP5299354B2 (ja) * | 2010-06-01 | 2013-09-25 | 株式会社日立プラントテクノロジー | ターボ形流体機械 |
US8834104B2 (en) * | 2010-06-25 | 2014-09-16 | Honeywell International Inc. | Vanes for directing exhaust to a turbine wheel |
EP2603703A1 (en) * | 2010-08-12 | 2013-06-19 | Nuovo Pignone S.p.A. | Radial diffuser vane for centrifugal compressors |
FR2976633B1 (fr) | 2011-06-20 | 2015-01-09 | Turbomeca | Procede de diffusion d'un etage de compression d'une turbine a gaz et etage de diffusion de mise en oeuvre |
-
2013
- 2013-03-28 FR FR1352829A patent/FR3003908B1/fr active Active
-
2014
- 2014-03-25 PL PL14718669T patent/PL2978977T3/pl unknown
- 2014-03-25 KR KR1020157030921A patent/KR102196815B1/ko active IP Right Grant
- 2014-03-25 JP JP2016504723A patent/JP6367917B2/ja not_active Expired - Fee Related
- 2014-03-25 EP EP14718669.6A patent/EP2978977B1/fr active Active
- 2014-03-25 ES ES14718669.6T patent/ES2606831T3/es active Active
- 2014-03-25 US US14/780,881 patent/US9890792B2/en active Active
- 2014-03-25 RU RU2015146262A patent/RU2651905C2/ru active
- 2014-03-25 WO PCT/FR2014/050693 patent/WO2014154997A1/fr active Application Filing
- 2014-03-25 CA CA2908081A patent/CA2908081C/fr active Active
- 2014-03-25 CN CN201480030172.1A patent/CN105247223B/zh not_active Expired - Fee Related
Non-Patent Citations (1)
Title |
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None * |
Also Published As
Publication number | Publication date |
---|---|
KR102196815B1 (ko) | 2020-12-30 |
CA2908081A1 (fr) | 2014-10-02 |
FR3003908B1 (fr) | 2017-07-07 |
CN105247223A (zh) | 2016-01-13 |
JP6367917B2 (ja) | 2018-08-01 |
WO2014154997A1 (fr) | 2014-10-02 |
EP2978977A1 (fr) | 2016-02-03 |
RU2015146262A3 (ko) | 2018-03-01 |
CA2908081C (fr) | 2020-11-24 |
US20160053774A1 (en) | 2016-02-25 |
RU2651905C2 (ru) | 2018-04-24 |
KR20150138291A (ko) | 2015-12-09 |
CN105247223B (zh) | 2017-05-17 |
JP2016514791A (ja) | 2016-05-23 |
RU2015146262A (ru) | 2017-05-04 |
PL2978977T3 (pl) | 2017-02-28 |
FR3003908A1 (fr) | 2014-10-03 |
US9890792B2 (en) | 2018-02-13 |
ES2606831T3 (es) | 2017-03-28 |
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