EP2623793A1 - Grille d'aubes et turbomachine - Google Patents

Grille d'aubes et turbomachine Download PDF

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Publication number
EP2623793A1
EP2623793A1 EP12153623.9A EP12153623A EP2623793A1 EP 2623793 A1 EP2623793 A1 EP 2623793A1 EP 12153623 A EP12153623 A EP 12153623A EP 2623793 A1 EP2623793 A1 EP 2623793A1
Authority
EP
European Patent Office
Prior art keywords
blade
blades
grid
turbomachine
angle
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
EP12153623.9A
Other languages
German (de)
English (en)
Other versions
EP2623793B1 (fr
Inventor
Roland Dr. Wunderer
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines GmbH
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 MTU Aero Engines GmbH filed Critical MTU Aero Engines GmbH
Priority to EP12153623.9A priority Critical patent/EP2623793B1/fr
Priority to US13/756,721 priority patent/US9404368B2/en
Publication of EP2623793A1 publication Critical patent/EP2623793A1/fr
Application granted granted Critical
Publication of EP2623793B1 publication Critical patent/EP2623793B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—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
    • F04D29/18—Rotors
    • F04D29/181—Axial flow rotors
    • 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
    • F04D29/18—Rotors
    • F04D29/22—Rotors specially for centrifugal pumps
    • F04D29/24—Vanes
    • F04D29/242—Geometry, shape
    • F04D29/245—Geometry, shape for special effects
    • 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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/325—Rotors specially for elastic fluids for axial flow pumps for axial flow fans
    • F04D29/327—Rotors specially for elastic fluids for axial flow pumps for axial flow fans with non identical 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
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/4206—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
    • F04D29/4213—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps suction ports
    • 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
    • F04D29/445—Fluid-guiding means, e.g. diffusers especially adapted for liquid pumps
    • F04D29/448—Fluid-guiding means, e.g. diffusers especially adapted for liquid pumps 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
    • 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
    • F04D29/42—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
    • F04D29/466—Fluid-guiding means, e.g. diffusers adjustable especially adapted for liquid 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
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—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
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • F04D29/544—Blade shapes
    • 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
    • F04D29/666—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by means of rotor construction or layout, e.g. unequal distribution of blades or vanes
    • 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
    • F05D2260/00—Function
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise
    • F05D2260/961—Preventing, counteracting or reducing vibration or noise by mistuning rotor blades or stator vanes with irregular interblade spacing, airfoil shape

Definitions

  • the invention relates to a blade grid for a turbomachine according to the preamble of patent claim 1 and a turbomachine.
  • turbomachines or turbo machinery especially in compressors and hydraulic pumps, but also in turbines, it comes in partial and overload operation to unstable flow conditions and greatly increased losses.
  • the unstable flow conditions lead to strong pressure fluctuations that can damage the blade structures.
  • the flow can completely collapse in compressors and hydraulic pumps in the throttled state. This limits the operating range of the turbomachine and can lead to damage to the turbomachine when exceeding the allowable limits.
  • Decisive for the unstable flow state is the separation of the flow of the individual blades in the lattice composite. To suppress the separation can lead to a time-varying inflow to the blades.
  • the blade affected by detachment oscillates about a suspension axis.
  • vibrating vanes are located in the inflow of the vanes affected by detachment, creating a harmonic, oscillating inflow to the vanes.
  • An example is a vibrating Vorleitbeschaufelung.
  • a further measure provides, by means of injection points distributed over the circumference, to introduce fluid which has a flow angle and / or flow impulse deviating from the main flow, thereby locally changing the inflow of the blades affected by detachment.
  • the object of the invention is to provide a blade grid for a turbomachine, which eliminates the aforementioned disadvantages and increases the operating range of turbomachines over the known measures. Furthermore, it is an object of the invention to provide a turbomachine with an enlarged operating range.
  • a vane grille according to the invention for a turbomachine has a multiplicity of vanes arranged in the circumferential direction next to one another, of which at least two adjacent vanes have different trailing edge angles according to the invention.
  • the blade grid is asymmetrical in the circumferential direction, whereby an asymmetrical outflow takes place due to the variation in the rear blade area and an asymmetrical inflow in the circumferential direction with respect to a flow angle and flow impulse to a downstream blade grid affected by detachment is thereby produced.
  • the separation behavior in the blade grid which follows the asymmetrical blade grid, is thereby suppressed.
  • the solution according to the invention makes it possible to expand the operating range in which a turbomachine can be operated and thereby ensure safe operation even in partial and overload. Furthermore, the flow losses are reduced by the asymmetric blade grid according to the invention and thus the efficiency is increased.
  • the Integration of the blade grid in a turbomachine can be done without additional installations and with little design measures. This allows the use of the blade grid in already designed turbomachines, without a re-interpretation of turbomachines is necessary.
  • the asymmetric arrangement according to the invention can be used in compressors or hydraulic pumps and in turbines, both in machines through which a gaseous and a liquid medium flows.
  • the blade grid can also be designed in an axial design, in a radial design or in a mixed diagonal design.
  • the blades are staggered circumferentially with respect to their leading blade over their entire height, so that the blades also have different leading edge angles.
  • the leading edge angle is changed by the same amount as the trailing edge angle. This embodiment allows the use of uniform or identical blades.
  • the blades are circumferentially differently staggered with respect to their leading blade over part of their height.
  • the blades each have at least two profile regions, which are located one behind the other in the transverse direction of the blade, and which are twisted relative to one another.
  • the blades thus have at least two different blade angle components each.
  • a blade angle portion of the non-staggered region is the same for all blades.
  • a vane angle portion of the redistributed region varies between the vanes and may increase or decrease, whereby the vanes in this region each have a modified trailing edge angle and a leading edge angle varied by the same amount.
  • the blades are profiled differently in the circumferential direction with respect to their leading blade over their entire height.
  • the blades are equally staggered with respect to their leading edges and thus have the same leading edge angle.
  • the trailing edge angles of the blades vary.
  • the blades have different curved trailing edge regions from a certain same chord length.
  • the blades are profiled differently in the circumferential direction with respect to their leading blade only over part of their height. This can be, for example, a local deformation of an outer region, viewed in the transverse direction of the blade, of the trailing edge, the orientation of which is changed in the circumferential direction over several blades of, for example, an orientation in the direction of rotation in an opposite direction.
  • the blade grid can cooperate with an adjusting device, so that the blades are adjustable in different degrees in the circumferential direction.
  • a preferred turbomachine has a symmetrical blade grid and an upstream asymmetric blade grid moving circumferentially relative to the symmetrical blade grid in accordance with the invention.
  • turbomachine has an increased operating range and a higher efficiency than conventional turbomachines.
  • the turbomachine may be a compressor, a hydraulic pump and a turbine.
  • the turbomachine can also be flowed through with any liquid or gaseous medium.
  • the turbomachine may have an adjusting device for staggering the blades of different degrees, which enables both the formation of a symmetrical blade grid and the formation of an asymmetrical blade grid.
  • the adjustment allows the control of each blade individually, whereby a maximum of flexibility in staggering is achieved.
  • predetermined symmetries and asymmetries can be set, which considerably simplifies the setting of the respective blade grid.
  • the asymmetric blade grid can be designed both as a stator grid and as a rotor grid.
  • When forming the blade grid according to the invention as a stator grid can have fixed blades or cooperate with an adjusting device for adjusting the blades.
  • blades are to be mounted in a blade grid of a turbomachine in such a way that that in the circumferential direction an asymmetrical outflow from the blade grid with respect to flow angle and flow velocity and thus takes place in the relative system of a subsequent blade grid an asymmetric inflow.
  • the following blade grid is symmetrical.
  • the asymmetrical outflow is generated by two or more adjacent blades have different trailing edge angles in the circumferential direction.
  • the vane grille according to the invention can be used in compressors or in hydraulic pumps and in turbines, both in machines through which gaseous and also liquid medium flows.
  • the trailing edge angle is understood to be an angle between a tangent of the skeleton line in the region of the trailing edge and an axis in the circumferential direction (see FIG. FIG. 4 , Angle ⁇ ).
  • the trailing edge angle ⁇ depends on the one hand on the blade profile in the rear blade area. On the other hand, the trailing edge angle ⁇ depends on the staggering of the respective blade in the blade grid and thus on the blade angle.
  • the blade angle or stagger angle is understood to mean an angle between the chord and the axis in the circumferential direction (see FIG. FIG. 2 , Angle ⁇ ).
  • the transverse direction of the blade is understood to mean an orientation of the blade between a rotor-side blade root and a blade tip. In axial compressors, the blade direction is equal to the radial direction. An extension of the blade in the transverse direction of the blade is understood across all construction types - axial, radial or diagonal construction - as a blade height.
  • the asymmetry can be realized by a plurality of measures, which are explained in more detail below with reference to the figures.
  • Preferred measures are a staggering over the entire blade height ( Figures 1 and 2 ), a staggering over a part of the blade height (also FIG. 2 ), a modified profiling over part of the blade height ( FIGS. 3 and 4 ) and a modified profiling over the entire blade height (also FIG. 4 ).
  • Figures 1 and 2 show a staggering over the entire blade height in a compressor stator in axial construction.
  • FIG. 2 is a sectional view, the sectional view can also show a staggering over a portion of the blade height.
  • the following is based on the Figures 1 and 2 a graduation over the entire blade height exemplified. For clarity, is in FIG. 2 only the blade angle ⁇ outlined.
  • An asymmetric blade grid 1 according to the invention has a multiplicity of blades 2 which are arranged next to one another in the circumferential direction.
  • the blade grid 1 is, for example, a part of a compressor stator in an axial construction.
  • the blades 2 have a uniform profile and are staggered differently in the circumferential direction with respect to their leading blade 2 'over their entire height.
  • the blade angle ⁇ varies starting from a blade angle ⁇ 0 which , compared to the leading blade 2 ', is increased ⁇ + or reduced ⁇ -.
  • the position of its trailing edges 4 changes in the circumferential direction, so that the same profiled adjacent blades 2 show a different outflow behavior.
  • the blades are 2 viewed by the pivoting with their trailing edges 4 in the circumferential direction no longer on a line, but are at different axial positions, whereby the discharge behavior is additionally changed.
  • leading edge angle is understood to mean an angle between a tangent of the skeleton line in the region of the front edge 8 and the axis in the circumferential direction (not sketched).
  • FIG. 3 shows an altered profiling over a part of the blade height in a compressor stator in axial construction.
  • the illustrated blade grid 1 forms part of a compressor stator in Axialbauweise.
  • the blades 2, viewed in the transverse direction of the blade are profiled differently in the outer region 6 of their trailing edges 4.
  • the region 6 turns from an orientation in the direction of rotation in an orientation in the opposite direction, whereby the trailing edge angle ⁇ of the blades 2, starting from a trailing edge angle ⁇ 0 relative to the respective leading blade 2 'to the circumferential direction increases ⁇ + or smaller ⁇ - is.
  • the trailing edge angle ⁇ is removed in the blades 2 at a uniform position in the transverse direction of the blade, wherein it is preferably removed in the region of the maximum profile change. Likewise, the blade angle ⁇ is preferably removed in the region of the maximum profile change.
  • Each blade 2 has a constant blade angle component ⁇ const and a varying blade angle component ⁇ var as a result of the local profiling relative to a flood track segment. Also, each blade 2 has a constant trailing edge angle component ⁇ const and a varying trailing edge angle component ⁇ var relative to a floodpath section.
  • the angle components ⁇ const , ⁇ const are the same and constant in the unchanged profile range in all blades 2.
  • FIG. 4 shows a modified profiling over the entire blade height.
  • FIG. 4 is a sectional view, the sectional view can also show a modified profiling over a portion of the blade height.
  • the following is based on FIG. 4 a modified profiling over the entire blade height exemplified.
  • the blades 2 have differently curved trailing edge regions 6 from a certain same chord length, whereby the trailing edge angle ⁇ of the blades 2 is increased ⁇ + or reduced ⁇ , starting from a trailing edge angle ⁇ 0 relative to the respective leading blade 2 '.
  • the adjacent blades 2 each have different profiles.
  • the area of their leading edges 8 is identically contoured, so that the blades 2 thus have the same leading edge angle.
  • the blade grids 1 can interact with an adjustment device, not shown, which enables a different degree of staggering of individual blades 2.
  • the asymmetrical arrangement of the blades 2 in the circumferential direction is preferably repeated several times periodically.
  • the flood track section shown here was placed in the transverse direction of the blade on the outer region of the blades 2.
  • the blade grid arrangement is chosen in particular such that a harmonic and periodic angular distribution is present.
  • any arrangement or profile design of the blades 2 can take place.
  • the minimum number of blades 2 per period is two.
  • the relevant size for the arrangement or profile design of a blade 2 is its outflow angle from the blade 2. The outflow angle is essentially dependent on the trailing edge angle ⁇ and thus on the blade angle ⁇ and the profile geometry, which is why, as in FIG. 6 shown, the trailing edge angle ⁇ as a size is used to describe the asymmetric blade grid assembly.
  • FIG. 6 seven examples of an asymmetrical arrangement of the blades 2 are shown with respect to the trailing edge angle ⁇ , wherein the embodiments 1, 2, 3 and 4 are preferred.
  • the number of blades 2 to be mounted within a period is determined by the following mutually equivalent formulations.
  • the maximum value difference for the arrangement or profile design of the blades 2 is a maximum of 20 °.
  • the angle difference is a maximum of 10 °.
  • FIGS. 7 and 8 show a section of a compressor stator in diagonal construction and FIG. 8 shows a section of a compressor stator in radial construction.
  • the blades 2 are numbered.
  • the invention can also be realized on the turbine side.
  • a blade grid for a turbomachine with a plurality of circumferentially juxtaposed blades wherein at least two blades in the rear region have a variation for generating an asymmetric outflow
  • a turbomachine, with an asymmetric blade grid, which is connected upstream of a further blade grid Disclosed are a blade grid for a turbomachine with a plurality of circumferentially juxtaposed blades, wherein at least two blades in the rear region have a variation for generating an asymmetric outflow
  • a turbomachine with an asymmetric blade grid, which is connected upstream of a further blade grid.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Geometry (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP12153623.9A 2012-02-02 2012-02-02 Turbomachine avec grille d'aubes Active EP2623793B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP12153623.9A EP2623793B1 (fr) 2012-02-02 2012-02-02 Turbomachine avec grille d'aubes
US13/756,721 US9404368B2 (en) 2012-02-02 2013-02-01 Blade cascade and turbomachine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP12153623.9A EP2623793B1 (fr) 2012-02-02 2012-02-02 Turbomachine avec grille d'aubes

Publications (2)

Publication Number Publication Date
EP2623793A1 true EP2623793A1 (fr) 2013-08-07
EP2623793B1 EP2623793B1 (fr) 2016-08-10

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US (1) US9404368B2 (fr)
EP (1) EP2623793B1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
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EP2993356A1 (fr) * 2014-09-02 2016-03-09 MAN Diesel & Turbo SE Étage de compresseur radial
EP3382147A1 (fr) * 2017-03-29 2018-10-03 United Technologies Corporation Ensemble d'aube asymétrique
US10208765B2 (en) 2015-01-28 2019-02-19 MTU Aero Engines AG Gas turbine axial compressor
DE102018119704A1 (de) * 2018-08-14 2020-02-20 Rolls-Royce Deutschland Ltd & Co Kg Schaufelrad einer Strömungsmaschine
CN110869619A (zh) * 2017-12-06 2020-03-06 三菱重工业株式会社 离心压缩机及涡轮增压器

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WO2014143290A1 (fr) * 2013-03-15 2014-09-18 United Technologies Corporation Aubes déversées pour moteurs à turbine à gaz
US20140286758A1 (en) * 2013-03-19 2014-09-25 Abb Turbo Systems Ag Nozzle ring with non-uniformly distributed airfoils and uniform throat area
US10584715B2 (en) * 2014-02-19 2020-03-10 United Technologies Corporation Gas turbine engine airfoil
JP6468414B2 (ja) 2014-08-12 2019-02-13 株式会社Ihi 圧縮機静翼、軸流圧縮機、及びガスタービン
WO2016100509A1 (fr) * 2014-12-16 2016-06-23 General Electric Company Diffuseur pour une pompe de compresseur à fluide à phases multiples
US10215194B2 (en) 2015-12-21 2019-02-26 Pratt & Whitney Canada Corp. Mistuned fan
CN108603513B (zh) * 2016-01-14 2020-08-25 三菱重工发动机和增压器株式会社 压缩机叶轮及其制造方法
US10670041B2 (en) 2016-02-19 2020-06-02 Pratt & Whitney Canada Corp. Compressor rotor for supersonic flutter and/or resonant stress mitigation
US10458436B2 (en) 2017-03-22 2019-10-29 Pratt & Whitney Canada Corp. Fan rotor with flow induced resonance control
US10480535B2 (en) 2017-03-22 2019-11-19 Pratt & Whitney Canada Corp. Fan rotor with flow induced resonance control
US10823203B2 (en) 2017-03-22 2020-11-03 Pratt & Whitney Canada Corp. Fan rotor with flow induced resonance control
CN109958659B (zh) * 2019-03-10 2021-04-02 江苏大学镇江流体工程装备技术研究院 一种具有导流结构的离心泵
JP7264685B2 (ja) * 2019-03-26 2023-04-25 三菱重工航空エンジン株式会社 タービン静翼、及びタービン
FR3099518B1 (fr) * 2019-07-31 2021-08-06 Safran Aircraft Engines Ensemble redresseur pour un compresseur de turbomachine

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EP2993356A1 (fr) * 2014-09-02 2016-03-09 MAN Diesel & Turbo SE Étage de compresseur radial
US10208765B2 (en) 2015-01-28 2019-02-19 MTU Aero Engines AG Gas turbine axial compressor
EP3382147A1 (fr) * 2017-03-29 2018-10-03 United Technologies Corporation Ensemble d'aube asymétrique
US10526905B2 (en) 2017-03-29 2020-01-07 United Technologies Corporation Asymmetric vane assembly
CN110869619A (zh) * 2017-12-06 2020-03-06 三菱重工业株式会社 离心压缩机及涡轮增压器
CN110869619B (zh) * 2017-12-06 2021-06-25 三菱重工业株式会社 离心压缩机及涡轮增压器
US11384766B2 (en) 2017-12-06 2022-07-12 Mitsubishi Heavy Industries Marine Machinery & Equipment Co., Ltd. Diffuser vane geometry for a centrifugal compressor and turbocharger
DE102018119704A1 (de) * 2018-08-14 2020-02-20 Rolls-Royce Deutschland Ltd & Co Kg Schaufelrad einer Strömungsmaschine
US11105207B2 (en) 2018-08-14 2021-08-31 Rolls-Royce Deutschland Ltd & Co Kg Wheel of a fluid flow machine
US11391169B2 (en) 2018-08-14 2022-07-19 Rolls-Royce Deutschland Ltd & Co Kg Wheel of a fluid flow machine

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US20130202444A1 (en) 2013-08-08

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