EP3183427A1 - Profiling of guide vanes of stators in turbomachinery, in particular compressors - Google Patents
Profiling of guide vanes of stators in turbomachinery, in particular compressorsInfo
- Publication number
- EP3183427A1 EP3183427A1 EP15775196.7A EP15775196A EP3183427A1 EP 3183427 A1 EP3183427 A1 EP 3183427A1 EP 15775196 A EP15775196 A EP 15775196A EP 3183427 A1 EP3183427 A1 EP 3183427A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- blade
- turbomachine
- profile
- airfoil
- compressor
- 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
Links
- 239000012530 fluid Substances 0.000 claims abstract description 25
- 230000001419 dependent effect Effects 0.000 claims description 5
- 230000005540 biological transmission Effects 0.000 claims description 3
- 238000011161 development Methods 0.000 description 7
- 230000018109 developmental process Effects 0.000 description 7
- 239000007789 gas Substances 0.000 description 6
- 230000006835 compression Effects 0.000 description 5
- 238000007906 compression Methods 0.000 description 5
- 238000000034 method Methods 0.000 description 5
- 230000008569 process Effects 0.000 description 5
- 230000007423 decrease Effects 0.000 description 4
- 238000000926 separation method Methods 0.000 description 3
- 238000010009 beating Methods 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 230000007246 mechanism Effects 0.000 description 2
- 238000011144 upstream manufacturing Methods 0.000 description 2
- 238000009423 ventilation Methods 0.000 description 2
- 241000937413 Axia Species 0.000 description 1
- 235000010678 Paulownia tomentosa Nutrition 0.000 description 1
- 240000002834 Paulownia tomentosa Species 0.000 description 1
- 230000003466 anti-cipated effect Effects 0.000 description 1
- 238000000354 decomposition reaction Methods 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 108090000623 proteins and genes Proteins 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 239000013589 supplement Substances 0.000 description 1
- 210000002435 tendon Anatomy 0.000 description 1
Classifications
-
- 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
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
- F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
- F01D17/165—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for radial flow, i.e. the vanes turning around axes which are essentially parallel to the rotor centre line
-
- 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
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
- F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
- F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
-
- 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
- F04D29/18—Rotors
- F04D29/22—Rotors specially for centrifugal pumps
- F04D29/24—Vanes
- F04D29/242—Geometry, shape
-
- 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
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
-
- 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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using 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
- F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
- F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors
-
- 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
- F04D29/287—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps with adjusting means
-
- 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
- F04D29/40—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
- F04D29/46—Fluid-guiding means, e.g. diffusers adjustable
- F04D29/462—Fluid-guiding means, e.g. diffusers adjustable especially adapted for elastic fluid 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
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
- F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially 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
- F05D2220/00—Application
- F05D2220/40—Application in turbochargers
-
- 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
- F05D2250/51—Inlet
-
- 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
- F05D2250/70—Shape
Definitions
- the invention relates to a distributor for a turbo ⁇ machine, in particular a compressor, as well as a turbo ⁇ machine with such constituatapparat.
- Compressors or fluid compressing devices are used in various industries for various applications involving compression or compression of (process) fluids, especially (process) gases.
- Known examples of this are turbo compressors in mobile industrial applications, such as in exhaust gas turbochargers or in
- Jet engines or even in stationary industrial applications, such as gearbox or gear turbo compressor for Heilzerlegung.
- a turbocompressor which operates continuously in its mode of operation, the pressure increase (compression) of the fluid is brought about by an angular momentum of the fluid from inlet to outlet through a rotating, radially extending impeller of the turbo-compressor due to the rotation of the blades is increased.
- a compressor stage to increase pressure and temperature of the fluid, while the relative (flow) decreases Ge ⁇ speed of the fluid in the impeller.
- a plurality of such compressor stages can be connected in series.
- turbocompressors As types of turbocompressors, a distinction is made between radial and axial compressors.
- the fluid to be compressed for example a process gas
- the fluid to be compressed flows in a direction parallel to the axis (axial direction) through the compressor.
- the gas flows axially into the impeller of the compressor stage and then outward (radial, radial Rich ⁇ tung) deflected.
- a flow diversion becomes necessary behind each stage.
- STC-GO Siemens com- pany turbo compressor
- turbomachinery with nozzles, such as - usually adjustable - (axial impeller) upstream materialsleitapparaten and / or (axial impeller) downstream Austrittsleitapparaten to provide.
- Such nozzles usually arranged in a ring, ge ⁇ optionally by means of a (VG) mechanical (angular) comparable adjustable blades with profiled, flow-impeding of the (process) fluid / -th blades on which an optimized flow guide through the turbomachine contribute.
- VG VG
- angular angular
- Such an inlet and outlet guide apparatus is known, for example, from DE 10 2012 216 656 A1. Also the
- Gear turbo compressor STC-GC has a decisionsleitappa ⁇ advice (before its first stage).
- - in the case of an adjustable prevailsleit- system - is so adjustable by means of such a ⁇ baumsleitapparates the axial (with respect to the impeller axis) entering the turbo-machine (process) fluid and its flow in terms of velocity and flow direction before an impact on the impeller or adjusted to the first impeller stage in response to a power demand on the turbomachine by the (angular) adjustment of the blades or the blades of the blade ring of the inlet guide.
- the fluid flow no longer follows a profile contour of the blades or blades, resulting in flow losses, efficiency losses and so on is associated with limitations on the (performance / flexibility) requirements for turbomachinery.
- the invention has for its object to improve disadvantages of the prior art and to realize in a simple and kos ⁇ ten redesigne way turbomachinery, which are flexibly mobile with high efficiencies.
- the object is achieved by a distributor for a turbo ⁇ machine, in particular for a compressor, and by a turbomachine with such a distributor with the features according to the respective independent claim.
- the distributor has at least one blade which can be flowed around by a fluid and has a blade.
- a curvature of a profile center line (also referred to as a skeleton line) of the airfoil has at least one point of inflection.
- an airfoil profile surface can be modified such that flow losses in a wide adjustment range of an (adjustable) blade can be reduced in the case of an adjustable distributor without a significant change in a 0 ° position of the airfoil / blade.
- the performance or performance data of a turbomachine in certain operating points can be improved.
- the curvature of the profile center line / skeleton line of the blade leaf has exactly one inflection point.
- airfoil here forms a profile similar to an S-bend-shaped profile (for wings, beispielswei ⁇ se in flying wings, winglets).
- S-blow comes from the fact that the profiled center line / skeleton line in the rear of the profile "S-shaped” facing up, whereby - here then at the airfoil - the flow - with swirl (which depends on a Expression of the "s-shaped course” or an "s-shaped” facing upwards
- Profile trailing edge is,) - flows from the airfoil.
- the curvature of the profile center line of the airfoil is two
- an expression of the curvature is dependent on an aerodynamic task, in particular of anticipated inflow conditions the airfoil and / or the impeller. Even more pro ⁇ filieren or geometries such as section thickness, tread depth and / or span of the airfoil can be designed depending or from corresponding case- ⁇ accordingly the aerodynamic task.
- a turning point reserves be understood, / the wel ⁇ surface the distance of the at least one turning point or the point of inflection - - underlay (the inflection point) may in this case - in the following referred to it is of a leading edge of the airfoil - projected on a chord of the blade ⁇ leaf ,
- a relative inflection point reserve is the inflection point reserve be ⁇ drawn on the length of the chord or on the tread depth.
- the strength of the curvature and / or the curvature are optimized so that the flow of the airfoil - with assumed Verstellwinkel - with a certain, intended swirl (to the impeller) flows, but the flow around the blade ⁇ blade (at the assumed adjustment angle) without a flow separation.
- the airfoil is designed such that a profile depth of the airfoil changes over its span (extension of the airfoil from a blade airfoil to a free airfoil end).
- the blade changes its Pro ⁇ tread depth between its airfoil root and its free Blade end.
- a blade ⁇ sheet in its outer dimensions may be formed approximately trapezoidal.
- the forming blade ⁇ leaf is designed such that over the span of the airfoil varying profile depth and the profile thickness (corresponding also maximum profile thickness) changes with it.
- the profile thickness ⁇ changes according to the profile depth change.
- the airfoil scales here (over the span) according to its tread depth (over the span).
- Relative maximum pro ⁇ fildicke here the maximum profile thickness is related to the tread depth
- maximum profile curvature and relative maxi ⁇ male profile curvature in this case the maximum profile curvature is related to the tread depth
- a plurality or a plurality of the blades are arranged in a ring. Put simply, the blades form a guide ring here.
- an adjusting device for adjusting the blade - or in the case of several of the, in particular ring-shaped arranged to a guide ring, blades such as to be provided for their adjustment.
- an (adjusting) mechanism can be provided, which can be adjusted according to a prescribed kinematics, a blade or all blades of a Leitkranzes.
- a motor unit such as an electric motor, can also be used.
- the diffuser is an entry (so also arrangable or angeord- net at an inlet of the fluid machine) or Austrittsleit ⁇ apparatus (as can also be arranged or arranged at an outlet of the fluid machine). This can then be arranged in particular at an inlet of the fluid machine or at an outlet of the fluid machine such that the inflow or the outflow into and out of the fluid machine (via the inlet / outlet guide apparatus) takes place axially.
- the distributor is arranged in the axial extension of an impeller shaft in the fluid machine, or a central distributor axis is arranged in axia ⁇ ler extension of the impeller shaft.
- the distributor can be used in the turbomachine, in particular in a compressor, such as a single-stage or multi-stage centrifugal compressor or a multi-stage transmission compressor, or in a turbine.
- a compressor such as a single-stage or multi-stage centrifugal compressor or a multi-stage transmission compressor
- the turbomachine in particular a compressor or a turbine, has the distributor (for example also after its developments).
- FIG. 2 shows a sketch of an adjustable blade of an inlet guide apparatus
- Blade of an inlet diffuser (section III - III).
- Embodiment profiling of vanes of nozzles for turbomachines, in particular of constitutive gas compressors
- FIG. 1 shows a section of a multi-shaft gear ⁇ compressor 10, for example, for HeilZerlegung, arranged with a arranged in a volute casing 14 (first)
- the The The The The devissleitapparat 1 has, as FIG 1 also verdeut ⁇ light, a plurality of annularly arranged, adjustable profiled blades 3 having guide vanes 4 (see FIG 2, FIG 3) on (Leitkranz 13, inlet guide 13).
- the control of the transmission compressor 10 is u.a. via the adjustable constitutionsleitapparat 1, i. by adjusting the blades 4 and their blades 3 (by means of an adjustment mechanism 12), which - depending on the adjustment angle of the blades 4 and the blades 3 of the inlet guide 13 - the arrival, flow and outflow of the
- Blades 3 through the operating gas 2 at the inlet ⁇ guide apparatus 1 and thus in succession to the inflow to or
- the blades 3 a special professional ⁇ lation 23, ie here an S-beating profile 23rd (with a simple "S-beat"), up.
- variable vane 4 the profiled blade 3 which on the Verstellme ⁇ mechanics 12 - is adjustable (win Kel) - only indicated here represented by a check circuit-wave 18 and a pin 24 and plates 25th
- the airfoil 3 is essentially trapezoidal in its outer dimensions, ie the tread depth 8 decreases continuously in the airfoil 3 over its span 9 (extension of the airfoil 3 from its airfoil foot 19 to its free airfoil end 20).
- the blade 3 changes, here reduced, its tread depth 8 between its Schaufelblattfuß 19 and its free blade end 20 and over its span. 9
- the profile thickness 11 decreases over the span 9 of the airfoil 3 in accordance with the decrease in the tread depth 8 (also).
- Relative maximum profile thickness here is the maximum profile thickness bezo ⁇ gene on the tread depth 8)
- maximum profile curvature and relative maximum profile curvature here is the maximum Pro ⁇ filwölbung based on the tread depth 8) remain - over the span 9 of the airfoil 3 - unchanged.
- FIG 3 shows the section through the III - III ge (in FIG 2) ⁇ identified (Strömungslinien-) profile cut by the blade 3 of the blade 4 of the stator 13 of the input steinsleitapparates 1, in short, the profile 23 of the airfoil.
- the blade 3, or its pro ⁇ fil 23 forms an S-bend-profile 23 (with a single "S-bend") - "s-shaped” curved with a (simple) profile center line 6 or skeleton line 6 - out. That is, the ( "S-shaped") curvature of 5 of the profile center ⁇ lline / skeleton line 6 of the airfoil 3 comprises - in this case - exactly one turning point 7, with the profile center ⁇ lline / skeleton line 6 in the front region of the profile 23, ie in the region of the front edge 21 of the blade 3, "S-shaped” downward and in the rear region of the profile 23, ie in the region of the trailing edge 22 of the airfoil 3.
- the flow around the profile 23 is here also dependent (or is particularly influenced) by an expression of the "s-shaped course” or the "S-beat” in the profile 23, dhua the course and the strength of the curvature 5 and the position of (here a - otherwise also number of turning points) inflection point 7 (inflection point reserve 28 (distance of the inflection point 7 - projected onto the chord 26 (profile ⁇ tendon 26 is just connecting line between the front 21 and trailing edge 22 of the profile 23) of the airfoil. 3 from a leading edge 21 of the airfoil 3).
- the expression of the "S-impact" profile 23 of the airfoil 3 (about which the flow conditions in the airfoil 3 can be influenced) is dependent on the aerodynamic task in the inlet guide 1 (optimization on the aerodynamic task (or the operating point)), in particular ⁇ sondere 15 of be provided flow conditions of the airfoil 3 and the impeller 27 of the (first) compression stage (at the operating point) Is -.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Geometry (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102014221362.2A DE102014221362A1 (en) | 2014-10-21 | 2014-10-21 | Profiling of vanes of nozzles in turbomachinery, in particular compressors |
PCT/EP2015/072915 WO2016062531A1 (en) | 2014-10-21 | 2015-10-05 | Profiling of guide vanes of stators in turbomachinery, in particular compressors |
Publications (2)
Publication Number | Publication Date |
---|---|
EP3183427A1 true EP3183427A1 (en) | 2017-06-28 |
EP3183427B1 EP3183427B1 (en) | 2019-06-12 |
Family
ID=54252306
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP15775196.7A Not-in-force EP3183427B1 (en) | 2014-10-21 | 2015-10-05 | Profiling of inlet guide vanes of radial compressors |
Country Status (6)
Country | Link |
---|---|
US (1) | US10634156B2 (en) |
EP (1) | EP3183427B1 (en) |
CN (1) | CN107109960B (en) |
DE (1) | DE102014221362A1 (en) |
RU (1) | RU2674844C2 (en) |
WO (1) | WO2016062531A1 (en) |
Families Citing this family (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20170152860A1 (en) * | 2015-11-30 | 2017-06-01 | Borgwarner Inc. | Compressor inlet guide vanes |
US10774650B2 (en) * | 2017-10-12 | 2020-09-15 | Raytheon Technologies Corporation | Gas turbine engine airfoil |
RU196070U1 (en) * | 2019-10-14 | 2020-02-14 | Публичное акционерное общество "КАМАЗ" | FLUID TRANSPORTATION SYSTEM |
JP2022094019A (en) | 2020-12-14 | 2022-06-24 | 三菱重工コンプレッサ株式会社 | Rotary machine |
Family Cites Families (13)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6457938B1 (en) * | 2001-03-30 | 2002-10-01 | General Electric Company | Wide angle guide vane |
US7255530B2 (en) * | 2003-12-12 | 2007-08-14 | Honeywell International Inc. | Vane and throat shaping |
EP1790830B1 (en) * | 2005-11-25 | 2019-03-27 | BorgWarner, Inc. | Turbocharger guide vane and turbocharger |
DE102008004014A1 (en) | 2008-01-11 | 2009-07-23 | Continental Automotive Gmbh | Guide vane for a variable turbine geometry |
EP2241722A1 (en) | 2009-04-14 | 2010-10-20 | Siemens Aktiengesellschaft | Inlet guide vane and compressor |
DE102010014556B4 (en) * | 2010-04-10 | 2013-01-03 | Mtu Aero Engines Gmbh | Guide vane of a compressor |
US8834104B2 (en) * | 2010-06-25 | 2014-09-16 | Honeywell International Inc. | Vanes for directing exhaust to a turbine wheel |
JP5866802B2 (en) * | 2011-05-26 | 2016-02-17 | 株式会社Ihi | Nozzle blade |
RU2470159C1 (en) | 2011-06-21 | 2012-12-20 | Общество с ограниченной ответственностью "Научно-исследовательский и опытно-конструкторский институт "АЭРОТУРБОМАШ" | Updated axial blower |
DE102012216656B3 (en) | 2012-09-18 | 2013-08-08 | Siemens Aktiengesellschaft | Adjustable diffuser |
KR101790421B1 (en) * | 2013-01-23 | 2017-10-25 | 컨셉츠 이티아이 인코포레이티드 | Structures and methods for forcing coupling of flow fields of adjacent bladed elements of turbomachines, and turbomachines incorporating the same |
FR3003908B1 (en) | 2013-03-28 | 2017-07-07 | Turbomeca | DIFFUSER WITH FINES OF A RADIAL OR MIXED COMPRESSOR |
DE102013225642B4 (en) * | 2013-12-11 | 2020-09-17 | Vitesco Technologies GmbH | Exhaust gas turbocharger with an adjustable guide grille |
-
2014
- 2014-10-21 DE DE102014221362.2A patent/DE102014221362A1/en not_active Withdrawn
-
2015
- 2015-10-05 US US15/517,347 patent/US10634156B2/en not_active Expired - Fee Related
- 2015-10-05 WO PCT/EP2015/072915 patent/WO2016062531A1/en active Application Filing
- 2015-10-05 EP EP15775196.7A patent/EP3183427B1/en not_active Not-in-force
- 2015-10-05 CN CN201580057843.8A patent/CN107109960B/en not_active Expired - Fee Related
- 2015-10-05 RU RU2017117286A patent/RU2674844C2/en active
Also Published As
Publication number | Publication date |
---|---|
CN107109960A (en) | 2017-08-29 |
DE102014221362A1 (en) | 2016-04-21 |
WO2016062531A1 (en) | 2016-04-28 |
CN107109960B (en) | 2019-07-09 |
EP3183427B1 (en) | 2019-06-12 |
RU2674844C2 (en) | 2018-12-13 |
US10634156B2 (en) | 2020-04-28 |
US20170306972A1 (en) | 2017-10-26 |
RU2017117286A (en) | 2018-11-23 |
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