WO2017137201A1 - Verdichterlaufschaufel, verdichter und verfahren zum profilieren der verdichterlaufschaufel - Google Patents
Verdichterlaufschaufel, verdichter und verfahren zum profilieren der verdichterlaufschaufel Download PDFInfo
- Publication number
- WO2017137201A1 WO2017137201A1 PCT/EP2017/050453 EP2017050453W WO2017137201A1 WO 2017137201 A1 WO2017137201 A1 WO 2017137201A1 EP 2017050453 W EP2017050453 W EP 2017050453W WO 2017137201 A1 WO2017137201 A1 WO 2017137201A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- chord
- compressor
- profile
- profile section
- curvature
- Prior art date
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
- F04D21/00—Pump involving supersonic speed of pumped fluids
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D19/00—Axial-flow pumps
-
- 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
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
- F04D29/324—Blades
-
- 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
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/38—Blades
- F04D29/384—Blades characterised by form
-
- 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
-
- 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
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05D2240/302—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor characteristics related to shock waves, transonic or supersonic flow
-
- 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
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05D2240/305—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the pressure side of a rotor blade
-
- 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
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05D2240/306—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the suction side of a rotor blade
Definitions
- the invention relates to a Ver Whyrlaufschaufei and a method for profiling the Ver Whyrlaufschaufei.
- An axial-flow compressor has at least one blade ring with a plurality of compressor blades for compressing a working fluid.
- Compressor blade has a radially inner subsonic section, in which the compression takes place by means of a deflection of the flow of the working medium.
- WEI terhin the compressor blade to a transonic section in which the compression for the most part by means of a shock wave, wherein the Ar ⁇ beitsmedium is delayed from supersonic velocity to Unterschallge ⁇ speed.
- Losses in the flow of the working medium in the transonic section occur, for example, in the compression ⁇ shock and by detachment of the boundary layer at the
- the object of the invention is therefore a
- the compressor blade according to the invention for a ⁇ Ver tight in axial construction has a blade profile having a transonic section and an extending portion in the transonic profile section of the Blade profile, which has on its suction side a concave suction side region and a convex suction side region which is disposed downstream of the concave suction side region, and which has on its pressure side a convex pressure side region and a concave pressure side region, which is arranged downstream of the convex pressure side region where ⁇ in the case of a curvature course on the pressure side of the profile section and a curvature profile on the suction side of the profile section applied in each case are continuous over a chord of the profile section, the positions of the minimum values of the curvature courses do not deviate from one another by more than 10% of the length of the chord and the positions of the maximum values of the profile chord
- a compressor rotor blade for a compressor for compressing a working medium in axial construction which has a blade ⁇ row with the compressor blades, wherein the compressor blades have a blade profile with a transonic section, has the steps: providing a geometric model of the blade profile, where ⁇ in the Blade profile has a profile section extending in the transonic section, and the Laufschau ⁇ felsch is set that sets a nominal operating condition of the compressor, a compression shock in which the working fluid is delayed from supersonic to Un ⁇ terschall embod; Specifying edge ⁇ conditions for the blade flow flowing around which occurs at the nominal operating condition; Changing the profile section such that the suction side has a concave suction side portion and a convex suction side portion disposed downstream of the concave suction side portion and having on its pressure side a convex pressure side portion and a concave pressure side portion downstream The curve of the convex pressure side region is arranged, wherein a curvature course on the pressure side of the profile section and a
- Verêtschaufei invention can be performed with a shorter length of its chord than is the case with conven- tional Ver Whyrlaufschaufei without thereby to accept Einbu ⁇ SEN of efficiency or a reduction of the Häbe ⁇ kingdom. It is preferable that in the convex Saugction Scheme the curvature multiplied by the length of the chord has a maximum value of 2 to 4 and in the konka ⁇ ven pressure side region of the curvature multiplied by the length of the chord has a maximum value of 1, 5 to 2.5.
- the point of the concave Saugieribe ⁇ empire with the minimum curvature when projecting perpendicular to the chord of the profile section on this one Pro ⁇ jectionhui sets that of the leading edge of the profile ⁇ section of 40% to 80%, in particular of 60 % to 75%, the length of the chord is removed. It is preferred that the point of the convex suction side region with the maximum curvature when projecting perpendicularly onto the profile chord of the profile section predetermines thereon a projection point which is from 70% to 95%, in particular 80% to 90%, of the leading edge of the profile section. , the length of the chord is removed. Each of these measures can further increase the efficiency of the compressor.
- the thickness of the profile section at all points of the profile section perpendicular to the chord is shorter than 2.5% of the length of the chord.
- the compressor according to the invention for compressing a working ⁇ medium has a blade row on which the
- Compressor blades has, wherein the blade row is set up that at a nominal operating condition of the compressor precompression of the working fluid current ⁇ on a compression shock, in which the working medium of supersonic speed to subsonic speed is ver ⁇ hesitated, and upstream of one of two adjacent
- the profile section on a cylinder surface ⁇ whose axis coincides with the axis of the compressor ⁇ , on a conical surface, whose axis with the axis of the Compressor coincides, is located on a S i flow area of the compressor or in a tangential plane of the compressor.
- the S i flow surface extends in the circumferential direction and in the axial direction of the axial flow machine and describes a surface that follows an idealized flow.
- the profile section is changed such that in the convex suction side area, the curve of the curve has a maximum value larger than the maximum value of the curve of the curve in the corresponding area of the conventional compressor blade.
- the profile section is preferably modified such that in the convex suction ⁇ lateral region of the curve of the curvature multiplied by the length of the chord has a maximum value which is from 2 to 4 and in the concave pressure side region of the curve of the curvature multiplied by the length of the chord Maximum value, which is from 1.5 to 2.5.
- the blade row is designed in such a way that at the nominal operating conditions, a maximum pre isentropic shock Mach number of 1.4, in particular of a maximum of 1.3, has ⁇ .
- the profile section is changed ⁇ changed such that the point of the concave Saugcons with the minimum curvature in vertical projection on the chord of the profile section specifies a projection point on this, the from the front edge of the profiled-section of 40% to 80 % of the length of the chord is removed.
- Figure 3 is a profile section of the invention
- FIG. 4 shows curves of the invention
- FIG 5 shows the Machiereverrough of Figure 2 with normalized lengths of the chords.
- the blade profile has a radially inner subsonic section and a radially outer transonic section, wherein in FIGS. 1 and 3 only the transonic section is shown.
- the blade profile has a profile section 21 which extends in the transonic section.
- the profile section 21 is located on a cylindrical surface whose
- Axis coincides with the axis of the compressor, on a Ke ⁇ gel surface whose axis coincides with the axis of the compressor coincides ⁇ on an S i flow area of the compressor or in a tangential plane of the compressor.
- the profile section 21 has a front edge 2, a rear edge ⁇ 3, a pressure side 4 and a suction side 5.
- a profile chord 22 is shown in FIG straight line from the leading edge 2 to the trailing edge 3 extends.
- FIG. 3 shows a skeleton line 23 which extends from the front edge 2 to the rear edge 3 and is always located centrally between the pressure side 4 and the suction side 5 in a direction perpendicular to the chord 22.
- FIG. 1 shows a two-dimensional flow distribution of a working medium flowing in the compressor in a region of the compressor.
- a blade row 15 with the compressor blades 1, one of the blade row 15 downstream guide blade row 16 and one of the rotor blade row ⁇ fel Herbert 15 upstream guide blade row 17 is shown.
- the profile section 21 has on its suction side 5 a concave suction side region 10, which is arranged at least partially upstream of a compression joint 18, which has a flow which is established in the compressor under a nominal operating condition of the compressor.
- the compression stroke 18 is arranged in the regions of the flow in FIG. 1 in which the Mach number decreases from higher than 1 to lower than 1.
- Figure 1 shows that in the rated operation condition of the compressor ⁇ a precompression of the Häme ⁇ diums upstream of the shock wave 18 and upstream of one of two adjacent compressor blades 1 limited flow channel is made.
- the compaction shock 18 is arranged downstream of a compaction shock, relative to the length of the chord 22, which would have a flow that is similar to that of a conventional one
- Compressor blade 1 may differ in that it is formed exclusively convex on its suction side 5, and would set in the nominal operating condition.
- Figure 2 shows a comparison of the Mach number curves of the Verreterlaufschaufei 1 and the Mach number curves of the conventional forth ⁇ Ver emphasizerlaufschaufei.
- Reference numeral 6 denotes the Machiereverlauf on the pressure side of the conventional Ver emphasizerlaufschaufei
- the reference numeral 7 is the Machiereverlauf on the suction ⁇ side of the conventional Ver emphasizerlaufschaufei
- the reference numeral 8 is the Machiereverlauf on the pressure side 4 of the compressor rotor 1
- the disturbanceszei ⁇ chen 9 is the Mach number distribution on the suction side 5 of the
- Compressor rotor 1 denotes.
- the compressor rotor 1 Due to the reduced losses and higher profile load in the subsonic region, a higher efficiency can be achieved with the compressor rotor 1 than with the conventional compressor rotor. As a result of the higher efficiency, the compressor rotor blade 1, as shown in FIG. 2, can be made shorter than the conventional compressor rotor blade , as a result of which losses due to friction of the working fluid on the piston are increased
- FIG. 4 shows a curvature profile 27 along the pressure side 4 and a curvature profile 28 along the suction side 5.
- Both curvature curves 27, 28 are continuous.
- About the Horizon ⁇ talachse 25 is the length of the chord 22 and the vertical axis 26, the curvature k multiplied by the length of the chord 22 is applied.
- the curvature k is defined as
- Concave suction side areas and convex pressure side areas are characterized by a negative sign of the curvature.
- Convex and concave pressure side Saugate Scheme ⁇ che characterized by a positive sign of the curvature.
- the curve of the curvature multiplied by the length of the chord 22 has a minimum value that is from -1.2 to -0.5.
- the profile section 21 has on its suction side 5 a first convex suction side region 11, which is arranged downstream of the concave suction side region 10.
- the profile section 21 has, on its suction side 5 to a ⁇ Saugate Society second convex 12, which is located upstream of the concave Saugonic Schemes 10th In the convex suction side region 11, the course of the
- Curvature has a maximum value which is greater than the maximum ⁇ value of the curve of the curvature in the corresponding region of the conventional Ver Whyrlaufschaufei, in particular, in the convex suction side region 11 of the curve of the curvature multiplied by the length of the chord 22 has a maximum value, from 2 to 4 is.
- the point of the concave Saugcons 10 with the minima ⁇ len curvature in vertical projection on the chord 22 of the profile section 21 sets a projection ⁇ point 24 on this, of the leading edge of the profile section 21 of 40% to 80% of the length of the chord 22 is removed.
- the point of the convex suction side region 11 with the maxima ⁇ len curvature in the vertical projection on the chord 22 of the profile section 21 are on this one projection ⁇ point 24, which removes from the leading edge of 21 of 80% to 100% of the length of the chord 22 is.
- the profiled section 21 has on its pressure side 4 a convex pressure-side region 14, which is arranged in a region which is arranged opposite the concave suction-side region 10.
- the compressor blade 1 is profiled as follows: providing a geometrical model of the blade profile, wherein the blade profile has a profile section 21 which extends in the transonic section and on a surface of revolution, the axis of which coincides with the axis of the compressor, on a conical surface, the axis of which coincides with the axis of the compressor, lies on an S i flow surface of the compressor or in a tan ⁇ gentialen plane of the compressor, and the blade ⁇ row 15 is set that sets a compression stroke 18 at a nominal operating condition of the compressor . in which the working medium is delayed from supersonic speed to subsonic speed; - Setting boundary conditions for a flow around the blade 14, 15, which occurs at the nominal operating condition;
- shock wave moves downstream by changing the Pro ⁇ filitess 18, can mathematically insbesonde- re be a finite volume method, or experimentally be ⁇ true.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
Claims
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
KR1020187025646A KR102206204B1 (ko) | 2016-02-10 | 2017-01-11 | 압축기 로터 블레이드, 압축기, 및 압축기 로터 블레이드를 프로파일링 하기 위한 방법 |
CN201780011074.7A CN108603509B (zh) | 2016-02-10 | 2017-01-11 | 压气机转子动叶、压气机及用于对压气机转子动叶仿形的方法 |
US16/075,731 US10837450B2 (en) | 2016-02-10 | 2017-01-11 | Compressor rotor blade, compressor, and method for profiling the compressor rotor blade |
JP2018541648A JP6715941B2 (ja) | 2016-02-10 | 2017-01-11 | 圧縮機動翼、圧縮機、および圧縮機動翼を輪郭形成するための方法 |
EP17700921.4A EP3390833B1 (de) | 2016-02-10 | 2017-01-11 | Verdichterlaufschaufel, verdichter und verfahren zum profilieren der verdichterlaufschaufel |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP16155063.7 | 2016-02-10 | ||
EP16155063.7A EP3205885A1 (de) | 2016-02-10 | 2016-02-10 | Verdichterlaufschaufel und verfahren zum profilieren der verdichterlaufschaufel |
Publications (1)
Publication Number | Publication Date |
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WO2017137201A1 true WO2017137201A1 (de) | 2017-08-17 |
Family
ID=55345743
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/EP2017/050453 WO2017137201A1 (de) | 2016-02-10 | 2017-01-11 | Verdichterlaufschaufel, verdichter und verfahren zum profilieren der verdichterlaufschaufel |
Country Status (6)
Country | Link |
---|---|
US (1) | US10837450B2 (de) |
EP (2) | EP3205885A1 (de) |
JP (1) | JP6715941B2 (de) |
KR (1) | KR102206204B1 (de) |
CN (1) | CN108603509B (de) |
WO (1) | WO2017137201A1 (de) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN111156195B (zh) * | 2020-01-07 | 2023-11-17 | 哈尔滨工程大学 | 一种压气机叶片前缘结构 |
Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2934259A (en) * | 1956-06-18 | 1960-04-26 | United Aircraft Corp | Compressor blading |
FR2551145A1 (fr) * | 1980-07-30 | 1985-03-01 | Onera (Off Nat Aerospatiale) | Etage de compresseur supersonique a aubes et procede de determination |
JPH08121390A (ja) * | 1994-10-25 | 1996-05-14 | Ishikawajima Harima Heavy Ind Co Ltd | 高速流体用の圧縮機翼形 |
Family Cites Families (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6116856A (en) * | 1998-09-18 | 2000-09-12 | Patterson Technique, Inc. | Bi-directional fan having asymmetric, reversible blades |
US7195456B2 (en) * | 2004-12-21 | 2007-03-27 | United Technologies Corporation | Turbine engine guide vane and arrays thereof |
JP5371578B2 (ja) | 2009-06-26 | 2013-12-18 | 三菱重工業株式会社 | タービンロータ |
EP2299124A1 (de) * | 2009-09-04 | 2011-03-23 | Siemens Aktiengesellschaft | Verdichterlaufschaufel für einen Axialverdichter |
FR2953571B1 (fr) * | 2009-12-07 | 2018-07-13 | Valeo Systemes Thermiques | Helice de ventilateur, en particulier pour vehicule automobile |
JP5502695B2 (ja) * | 2010-10-14 | 2014-05-28 | 株式会社日立製作所 | 軸流圧縮機 |
EP2669475B1 (de) * | 2012-06-01 | 2018-08-01 | Safran Aero Boosters SA | S-Profil-Laufschaufel für Verdichter einer axialen Strömungsmaschine, zugehöriger Verdichter und Strömungsmaschine |
DE102013209966A1 (de) * | 2013-05-28 | 2014-12-04 | Honda Motor Co., Ltd. | Profilgeometrie eines Flügels für einen Axialkompressor |
EP3088663A1 (de) * | 2015-04-28 | 2016-11-02 | Siemens Aktiengesellschaft | Verfahren zum profilieren einer schaufel |
-
2016
- 2016-02-10 EP EP16155063.7A patent/EP3205885A1/de not_active Withdrawn
-
2017
- 2017-01-11 EP EP17700921.4A patent/EP3390833B1/de active Active
- 2017-01-11 JP JP2018541648A patent/JP6715941B2/ja active Active
- 2017-01-11 KR KR1020187025646A patent/KR102206204B1/ko active IP Right Grant
- 2017-01-11 US US16/075,731 patent/US10837450B2/en active Active
- 2017-01-11 CN CN201780011074.7A patent/CN108603509B/zh active Active
- 2017-01-11 WO PCT/EP2017/050453 patent/WO2017137201A1/de active Application Filing
Patent Citations (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2934259A (en) * | 1956-06-18 | 1960-04-26 | United Aircraft Corp | Compressor blading |
FR2551145A1 (fr) * | 1980-07-30 | 1985-03-01 | Onera (Off Nat Aerospatiale) | Etage de compresseur supersonique a aubes et procede de determination |
JPH08121390A (ja) * | 1994-10-25 | 1996-05-14 | Ishikawajima Harima Heavy Ind Co Ltd | 高速流体用の圧縮機翼形 |
Also Published As
Publication number | Publication date |
---|---|
KR102206204B1 (ko) | 2021-01-22 |
JP6715941B2 (ja) | 2020-07-01 |
EP3205885A1 (de) | 2017-08-16 |
EP3390833A1 (de) | 2018-10-24 |
KR20180110054A (ko) | 2018-10-08 |
EP3390833B1 (de) | 2019-09-04 |
JP2019504962A (ja) | 2019-02-21 |
CN108603509B (zh) | 2020-04-03 |
US10837450B2 (en) | 2020-11-17 |
CN108603509A (zh) | 2018-09-28 |
US20190048880A1 (en) | 2019-02-14 |
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