EP3351726A1 - Aube rotorique ou statorique pour compresseur et compresseur avec une telle aube - Google Patents

Aube rotorique ou statorique pour compresseur et compresseur avec une telle aube Download PDF

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Publication number
EP3351726A1
EP3351726A1 EP18152639.3A EP18152639A EP3351726A1 EP 3351726 A1 EP3351726 A1 EP 3351726A1 EP 18152639 A EP18152639 A EP 18152639A EP 3351726 A1 EP3351726 A1 EP 3351726A1
Authority
EP
European Patent Office
Prior art keywords
blade
face
appendix
vane
vane according
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
EP18152639.3A
Other languages
German (de)
English (en)
Other versions
EP3351726B1 (fr
Inventor
Marco TAPPANI
Andrea Schneider
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.)
Ansaldo Energia SpA
Original Assignee
Ansaldo Energia SpA
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 Ansaldo Energia SpA filed Critical Ansaldo Energia SpA
Publication of EP3351726A1 publication Critical patent/EP3351726A1/fr
Application granted granted Critical
Publication of EP3351726B1 publication Critical patent/EP3351726B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F04D29/26—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
    • 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
    • F01D5/145—Means for influencing boundary layers or secondary circulations
    • 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
    • F04D29/32—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
    • F04D29/40—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
    • F04D29/68—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
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/122—Fluid guiding means, e.g. vanes related to the trailing edge of a stator vane
    • 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
    • F05D2240/304—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 trailing edge 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
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/10—Purpose of the control system to cope with, or avoid, compressor flow instabilities
    • F05D2270/101—Compressor surge or stall

Definitions

  • the invention relates to a blade or vane for a compressor and to a compressor comprising said blade or vane.
  • the invention relates to a blade or vane for a compressor of a gas turbine power plant.
  • Gas turbine power plants usually comprise a compressor, where an air flow flows, a combustion chamber, which is supplied with a fuel and with air coming from the compressor, a gas turbine, where the gases coming from the combustion chamber flow, and a generator, which is mechanically connected to a common shaft of the gas turbine and of the compressor ad is connected to an electrical distribution network.
  • the compressor and the gas turbine extend along a longitudinal axis and respectively define a compression channel and an expansion channel, along which radial series of rotor blades, which rotate around the axis, alternate with radial series of stator vanes.
  • stall conditions can occur in the area of the aerofoil profile of the rotor blades or stator vanes. These conditions can cause instability phenomena, up to the surging of the entire compressor.
  • the operation of the plant is usually limited so as to prevent this phenomenon from occurring.
  • the operation of the compressor can be restricted by limiting the value of the minimum air flow rate of the compressor to a safety value that exceeds the minimum values that can actually be borne by the compressor in order to ensure the operation thereof.
  • an object of the invention is to provide a blade or vane for a compressor, which is not affected by the drawbacks of the prior art; in particular, an object of the invention is to provide blade or vane for a compressor, which allows users to optimally and safely exploit the potentialities of the compressor in an easy and economic manner, both from the functional point of view and from the constructive point of view.
  • the invention relates to a blade or vane for a compressor comprising:
  • a further object of the invention is to provide a compressor, which is reliable and, at the dame time, efficient.
  • the invention relates to a compressor for a power plant as claimed in claim 16.
  • number 1 indicates a gas turbine power plant.
  • the plant 1 extends along a longitudinal axis A and comprises a combustion chamber 2, a stator 3 and a rotor 4, which rotates around the axis A.
  • the stator 3 comprises a stator casing 5, which extends around the axis A over the entire length of the rotor 4 and is static, a plurality of stator rings 6, which are centred on the axis A, are supported by the stator casing 5 and are arranged in succession along the axis A, and a plurality of stator vanes 7, which substantially extend along respective radial directions and are fixed to the stator casing 5 and to the respective stator rings 6.
  • the rotor 4 comprises a shaft 8 extending along the axis A, a plurality of rotor discs 9, which are coupled to one another so as to define one single element rotating around the axis A, and a plurality of rotor blades 10, which are divided into series and are arranged radially with respect to the axis A.
  • stator rings 6 extend around the rotor discs 9 and are spaced apart from one another so that, along the axis A, radial series of rotor blades 10 alternate with radial series of stator vanes 7.
  • Said plurality of rotor discs 9, the stator rings 6 and the stator casing 5 define a compression channel 13a, where the air to be supplied in compression to the combustion chamber 2 flows, and an expansion channel 14a, where the hot gases coming from the combustion chamber 2 flow.
  • the compression channel 13, the stator rings 6, the rotor discs 9 and the stator casing 5, which surround the compression channel 13, define the so-called compressor 13a.
  • the expansion channel 14, the stator rings 6, the rotor discs 9 and the stator casing 5, which surround the expansion channel 14, define the so-called turbine 14a.
  • the direction of the air flow is schematically shown by the arrow indicated with F.
  • Each stage comprises a series of stator vanes 7 and a series of rotor blades 10.
  • Figure 2 schematically shows a portion of a stage of the compressor 13b, though without indicating in detail, for the sake of simplicity, all the aspects of the invention.
  • Each stator vane 7 of the compressor 13b comprises a main body 15, which is provided with a base face 16 coupled - in use - to the respective stator ring 6, with a top face 17 opposite the base face 16 and coupled - in use - to the stator casing 5, and with an outer face 18, which extends between the base face 16 and the top face 17 and defines the airfoil profile of the stator vane 7.
  • the base face 16 is proximal to the axis A with respect to the top face 17 along the radial direction of extension of the stator vane 7.
  • Each rotor blade 10 of the compressor comprises a main body 25, which is provided with a base face 26 coupled - in use - to the respective rotor disc 9, with a top face 27, which is free and opposite the base face 26, and with an outer face 28, which extends between the base face 26 and the top face 27 and defines the airfoil profile of the rotor blade 10.
  • the top face 27 is often defined "apex”.
  • the base face 26 is proximal to the axis A with respect to the top face 27 along the radial direction of extension of the rotor blade 10.
  • Figure 3 and figure 4 show a portion of the stator vane 7 according to the invention.
  • the vane 7 comprises the main body 15 described above and at least one appendix 29.
  • the main body 15 for the sake of simplicity, is represented like a solid body. However, the main body 15 can also be hollow.
  • the main body 15 is shaped so as to define, along the outer face 18 a leading edge 30, a trailing edge 31, a pressure side 32 and a suction side 33.
  • the main body 15 has a radial height S (shown in figure 3 ), usually defined in the field as “span”, an axial length C (shown in figure 4 ), usually defined in the field as “chord”, and a median line M (shown with a broken line in figure 4 ), usually defined in the field as "camber line”.
  • the appendix 29 is coupled to the main body 15 in the proximity of the trailing edge 31.
  • the appendix 29 is arranged at a distance from the trailing edge 31 that is smaller than 20% of the axial length C.
  • the appendix 29 is arranged exactly in the area of the trailing edge 31 and, therefore, in this example the distance from the trailing edge 31 is substantially equal to zero.
  • appendix we mean a projection of the body, for example shaped like a wing, or a portion of the body itself, which is properly bent and/or shaped so as to obtain the specific aerodynamic effect described hereinafter.
  • the appendix 29 is arranged along the pressure side 32 in the proximity of the top face 17. In other words, the appendix 29 is arranged at a distance from the top face 17 that is smaller than 30% of the radial height S.
  • the appendix 29 is arranged exactly in the area of the top face 17 and, therefore, in this example the distance from the top face 17 is substantially equal to zero.
  • the appendix 29 extends along at least a portion of the trailing edge 31.
  • the appendix 29 has a radial height S1 that is equal to at least 2% of the radial height S of the main body 15.
  • the appendix 29 tapers towards the centre of the main body 15.
  • Figure 5 shows an axial section of the main body 15 in the area of plane V-V indicated in figure 3 .
  • the appendix 29 has a substantially trapezoidal axial section.
  • the appendix 29 has a front face 40, a rear face 41 and an intermediate face 42 comprised between the rear face 41 and the front face 40.
  • the position of the front face 40 and of the rear face 41 relates to the direction of the working fluid air flow in the compression channel 13.
  • the front face 40 indeed, is the face that first meets the working fluid air flow in the compression channel 13.
  • the front face 40 is flat. According to a variant thereof, the front face is curved.
  • the front face 40 projects from the pressure side 32 and is arranged so that the tangent in at least one point of the front face 40 intersects the median line M (camber line) forming an angle ⁇ that is greater than 10°, preferably greater than 30°.
  • the tangent in at least one point of the front face 40 is the prolongation of the front face 40 itself.
  • the rear face 41 is flat. According to a variant thereof, the rear face is curved.
  • the rear face 41 projects from the trailing edge 31 and is arranged so that the tangent in at least one point of the rear face 41 intersects the median line M (camber line) forming an angles ⁇ that is greater than 30°, preferably greater than 50°.
  • the tangent in at least one point of the rear face 41 is the prolongation of the rear face 41 itself.
  • the rear face has a width L, meaning the measure of the extension of the rear face 41 along a direction orthogonal to the median line M with respect to the pressure side 32, that is smaller than 10% of the axial length C (chord).
  • the angle ⁇ is approximately 80° and the angles ⁇ is approximately 90°.
  • the intermediate face 42 is flat. According to a variant thereof, the intermediate face is curved.
  • the main body 15 and the appendix 29 are manufactured as one single piece.
  • the main body 15 and the appendix 29 are a one-piece body.
  • the appendix 29 is shaped so as to obtain a specific aerodynamic effect in the compression channel 13a, namely redistributing the working fluid flow rate on the blade or vane, moving the excess flow rate present on the central section of the main body 15 towards the end section of the main body 15 close to the top face 17. By so doing, stall is avoided even in operating conditions that would be impossible for traditional blades or vanes.
  • Figure 6 shows a stator vane 70 according to a second embodiment of the invention.
  • the same reference numbers used in the preceding figures 3-5 can be found to indicate parts that are substantially identical or similar.
  • the vane 70 basically differs from the vane 7 because it comprises an appendix 79 that is arranged in the proximity of the base face 16, instead of in the proximity of the top face 17.
  • the appendix 79 is arranged at a distance from the base face 16 that is smaller than 30% of the radial height S.
  • the appendix 79 is arranged exactly in the area of the base face 16 and, therefore, in this example the distance from the base face 16 is substantially equal to zero.
  • the appendix 79 has a radial height S2 that, again, is equal to at least 2% of the radial height S of the main body 15 and substantially has the same geometry as the appendix 29.
  • the appendix 79 is shaped so as to obtain a specific aerodynamic effect in the compression channel 13a, namely redistributing the working fluid flow rate on the blade or vane, moving the excess flow rate present on the central section of the main body 15 towards the end section of the main body 15 close to the base face 16. By so doing, stall can be avoided even in operating conditions that would be impossible for traditional blades or vanes.
  • Figure 7 shows a stator vane 700 according to a third embodiment of the invention.
  • the same reference numbers used in the preceding figures 3-5 can be found to indicate parts that are substantially identical or similar.
  • the vane 700 basically differs from the vane 7 because it comprises a further appendix 779 that is arranged in the proximity of the base face 16.
  • the appendix 29 is arranged at a distance from the top face 17 that is smaller than 30% of the radial height S, whereas the appendix 779 is arranged at a distance from the base face 16 that is smaller than 30% of the radial height S.
  • the appendix 29 is arranged exactly in the area of the top face 17 and, therefore, in this example the distance from the top face 17 is substantially equal to zero
  • the appendix 779 is arranged exactly in the area of the base face 16 and, therefore, in this example the distance of the appendix 779 from the base face 16 is substantially equal to zero.
  • the appendix 779 has a radial height S2 that, again, is equal to at least 2% of the radial height S of the main body 15 and substantially has the same geometry as the appendix 29.
  • the appendix 29 and the appendix 779 have different geometries, so as to determine different and targeted flow deflecting effects.
  • the appendices 29 and 779 are shaped so as to obtain a specific aerodynamic effect in the compression channel 13a, namely redistributing the working fluid flow rate on the blade or vane, moving the excess flow rate present on the central section of the main body 15 towards the end sections of the main body 15 close to the top face 17 and to the base face 16.
  • stall can be avoided even in operating conditions that would be impossible for traditional blades or vanes.
  • the blades or vanes 7, 10, 70, 700 according to the invention are capable of significantly increasing the flow deflection capacity in the proximity of one end or both ends of the main body 15, 25. By so doing, stall can be avoided even in operating conditions that would be impossible for traditional blades or vanes.
  • the appendices 29, 79, 779 are capable of redistributing the working fluid flow rate on the blade or vane 7, 10, 70, 700, moving the excess flow rate present on the central section towards one or more end sections of the main body 15, 25.
  • the risk of stall increases in the area of the ends.
  • the airfoil profiles of the blades or vanes of a compressor operate in different conditions in the central portion of the profile and at the two radial ends. In the aforesaid end areas, the blades or vanes cannot generate a deflection of the flow that is sufficient to make sure that the flow adheres to the profile, hence the function of the entire blade or vane is jeopardized.
  • the adherence of the flow to the profile of a blade or vane, or the lack thereof, depends on the shape of the blade or vane profile, on the speed of the flow and on the presence of viscous frictions, vortices and other disturbing aerodynamic phenomena.
  • the airfoil profile i.e. the outer face 18, 28 of the main body 15, 25
  • the airfoil profile is not changed in terms of curvature, axial or radial dimensions.
  • the simple addition of one or more appendices determined an increase in the capacity of the blade or vane of redistributing the flow rate from the central section to the end one, given the same surface. This is determined by a significant increase in the lift of the end sections, though with a low resistance increase.
  • the blade or vane acts as if its axial length (chord) were longer.
  • Chord axial length
EP18152639.3A 2017-01-19 2018-01-19 Aube rotorique ou statorique pour compresseur et compresseur avec une telle aube Active EP3351726B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
IT102017000005808A IT201700005808A1 (it) 2017-01-19 2017-01-19 Pala per un compressore e compressore comprendente detta pala

Publications (2)

Publication Number Publication Date
EP3351726A1 true EP3351726A1 (fr) 2018-07-25
EP3351726B1 EP3351726B1 (fr) 2020-05-13

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP18152639.3A Active EP3351726B1 (fr) 2017-01-19 2018-01-19 Aube rotorique ou statorique pour compresseur et compresseur avec une telle aube

Country Status (3)

Country Link
EP (1) EP3351726B1 (fr)
CN (1) CN108343637B (fr)
IT (1) IT201700005808A1 (fr)

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0615903A1 (fr) * 1993-03-13 1994-09-21 Westland Helicopters Limited Pales tournantes
EP0833060A2 (fr) * 1996-09-30 1998-04-01 Kabushiki Kaisha Toshiba Aube pour machine axiale à fluide
EP1112928A2 (fr) * 1999-12-31 2001-07-04 DLR Deutsches Zentrum für Luft- und Raumfahrt e.V. Profil aérodynamique avec bord de fuite améliorant la performance
EP2336492A1 (fr) * 2009-12-16 2011-06-22 Siemens Aktiengesellschaft Aube de guidage avec ailette pour machine de conversion d'énergie et machine pour convertir l'énergie comportant l'aube de guidage
US20160348694A1 (en) * 2015-05-26 2016-12-01 Pratt & Whitney Canada Corp. Gas turbine stator with winglets

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105756975B (zh) * 2016-04-26 2018-02-27 浙江理工大学 一种叶片前缘带凹槽结构和叶根吹气的轴流风机

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0615903A1 (fr) * 1993-03-13 1994-09-21 Westland Helicopters Limited Pales tournantes
EP0833060A2 (fr) * 1996-09-30 1998-04-01 Kabushiki Kaisha Toshiba Aube pour machine axiale à fluide
EP1112928A2 (fr) * 1999-12-31 2001-07-04 DLR Deutsches Zentrum für Luft- und Raumfahrt e.V. Profil aérodynamique avec bord de fuite améliorant la performance
EP2336492A1 (fr) * 2009-12-16 2011-06-22 Siemens Aktiengesellschaft Aube de guidage avec ailette pour machine de conversion d'énergie et machine pour convertir l'énergie comportant l'aube de guidage
US20160348694A1 (en) * 2015-05-26 2016-12-01 Pratt & Whitney Canada Corp. Gas turbine stator with winglets

Also Published As

Publication number Publication date
IT201700005808A1 (it) 2018-07-19
CN108343637B (zh) 2022-11-08
CN108343637A (zh) 2018-07-31
EP3351726B1 (fr) 2020-05-13

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