EP2721305B1 - Verfahren zum diffundieren einer gasturbinenkompressionsstufe und diffusionsstufe zur durchführung des verfahrens - Google Patents

Verfahren zum diffundieren einer gasturbinenkompressionsstufe und diffusionsstufe zur durchführung des verfahrens Download PDF

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Publication number
EP2721305B1
EP2721305B1 EP12734964.5A EP12734964A EP2721305B1 EP 2721305 B1 EP2721305 B1 EP 2721305B1 EP 12734964 A EP12734964 A EP 12734964A EP 2721305 B1 EP2721305 B1 EP 2721305B1
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European Patent Office
Prior art keywords
blades
plates
zones
diffusion
bump
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.)
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Application number
EP12734964.5A
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English (en)
French (fr)
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EP2721305A1 (de
Inventor
Laurent Tarnowski
Nicolas BULOT
Jérôme PORODO
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.)
Safran Helicopter Engines SAS
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Safran Helicopter Engines SAS
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Priority to PL12734964T priority Critical patent/PL2721305T3/pl
Publication of EP2721305A1 publication Critical patent/EP2721305A1/de
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    • 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
    • F04D19/002—Axial flow fans
    • 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
    • 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
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/50—Inlet or outlet
    • F05D2250/52—Outlet

Definitions

  • the invention relates to a diffusion stage of a radial or mixed compressor of a gas turbine.
  • the field of the invention relates to improving the performance and the pumping margin of centrifugal and mixed compressors on the diffusion assembly of the stage concerned.
  • the function of this diffusion assembly is to transform the kinetic energy of the fluid, obtained at the outlet of the centrifugal wheel constituting the stage, into static pressure.
  • the operation must take place with a minimum of total pressure loss while maintaining a satisfactory level of compressor stability in order to maintain an acceptable pumping margin for the operation of the turbomachine.
  • a centrifugal compressor has at least one radial compression stage, that is to say capable of producing an air flow perpendicular to the central axis of the compressor.
  • a mixed compressor has at least one compression stage inclined relative to said central axis.
  • a diffusion assembly with a compression stage is composed of a wheel formed by two flanges between which the fluid flows in a centrifugal or inclined manner from the center to the periphery.
  • the vanes are distributed between the flanges all along the wheel. These blades form a flow grid between the leading edges of these blades on the center side and the trailing edges on the outer side.
  • the flanges of the radial and mixed diffusion assemblies are traditionally planar and the fluid passage sections between the vanes are advantageously scalable.
  • the changes in the passage sections are defined by the passage section at the diffuser neck and by the level of deceleration between the leading and trailing edges of the blade grid.
  • the aim of the invention is to achieve such a flow by installing flanges optimized in shape because these flanges represent the largest surface “wetted” by the flow.
  • Non-axisymmetric shapes in the direction of flow and tangentially are thus proposed.
  • the present invention relates to a diffusion stage of a radial or mixed compressor of a gas turbine according to claim 1.
  • the three-dimensional shape of the stream of the fluid makes it possible to redistribute and homogenize its flow in this stream: the secondary flows, which generate pressure losses, are appreciably reduced.
  • the position of the shocks in the transonic vanes is modified and their weakened intensity.
  • the aerodynamic blocking at the inlet of the combustion chamber which follows the compression stage is also significantly reduced.
  • the diffusion stage has alternating hollow and hump zones between the blades, in particular up to substantially 80% (preferably up to substantially 50%) of a chord of a blade, at the leading edge of the blades, with a start upstream of the leading edge, and / or, according to an advantageous feature, at the trailing edge, downstream of the trailing edge.
  • These alternating areas of hollow and bump can be applied to one and / or the other of the two centrifugal (radial) and mixed diffusion flanges, in particular symmetrically, with respect to a central plane of symmetry of the flanges, or in a parallel manner in the case where the two flanges of the stage are concerned.
  • downstream and upstream qualify positions relative to the flow of the air flow.
  • identical reference signs refer to the passages of the description in which the elements corresponding to these reference signs are defined.
  • an air flow F is first sucked into a fresh air inlet sleeve 2, then compressed between the blades 3 of an impeller 4 of a centrifugal compressor 5 and a cover 10.
  • the turbine is axially symmetrical around an X'X axis.
  • the compressor 5 is here centrifugal and the compressed flow F then exits radially from the impeller 4.
  • the flow comes out inclined at an angle between 0 ° and 90 ° with respect to a radial direction, perpendicular to the axis X'X.
  • the flow F then passes through a diffuser or wheel 6, arranged at the outlet of the compressor 4, to be straightened and conveyed to the inlet channels 7 of a combustion chamber 8.
  • the wheel 6 consists of a plurality of curved blades 60, arranged between two flanges 9 at the periphery of the impeller 4 - here radially - and therefore of revolution about the axis X'X.
  • each blade 60 has, in a known manner, a face called the upper surface 6e and a face called the lower surface 6i. In the example illustrated, these faces are connected by a tapered leading edge 6a and a rounded trailing edge 6f, in the direction of flow of the air flow. Transversely to the upper and lower surfaces, each blade 60 has flat sides 6p secured to the side plates 9.
  • the flanges 9 of figures 2a and 2b are classically flat. According to the invention, at least one of these flanges 9 has, in the space E which they define between them, at least one region of alternating curvature between two blades 60.
  • such a flange 9 is illustrated in profile, in the direction of flow of the air flow F along the vanes 60, from the entry at the leading edge 6a of the vane to the outlet channel 7 towards the combustion chamber.
  • Two zones of alternating curvature Z1 and Z2 are produced in the flange 9, along the vanes 60. Each of these zones has, on the side of the flow F, and with respect to the flat face portion 9p of the flange 9, a recessed portion 91 and a humped portion 92.
  • the zones Z1 and Z2 extend overall, in the non-limiting example illustrated, over approximately 80% of the length of the chord 6c of the blades 60.
  • the flange 9 has in the figures a filiform thickness to simplify the presentation, but it actually has a certain thickness and the zones of alternating curvature are formed on the internal face 9i of the flange where the air flow F.
  • outer face 9e of the flange 9 can remain flat or also match shapes with alternating bump and hollow curvature, reversed in this example with respect to the hollow and bump shapes of the inner face 9i.
  • the flange has a variable thickness and, in the second case, a constant thickness.
  • the shape of the flanges may depend in particular on the method used to produce the areas of alternating curvature: by milling, laser, electroerosion, forming, stamping, etc.
  • the two zones of alternating curvature Z1 and Z2 are respectively formed at the trailing edge 6f of the blades 60 and downstream vanes in the inlet of channel 7, and on the leading edge 6a from the upstream inlet of the vanes 60.
  • the figure 4 illustrates a partial schematic view of the inter-vane “tangential direction” diffusion stage 6t, that is to say between two vanes 60.
  • the arrow F indicates the direction of air flow.
  • the internal face 9i of the flange 9 has two zones of alternating curvature Z1 and Z2 which extend mainly between the lower surface 6i and upper surface 6th two blades 60.
  • the inter-blade perspective view at the leading edge 6a of the figure 5 shows, more precisely, the flange 9 with a zone of alternating curvature Z1 between the two blades 60.
  • the zone has the portion with recessed curvature 91, at the lower surface 6i of a blade 60, and the portion with hump curvature 92, at the 6th upper surface of the other vane 60. This alternation of curvatures balances the pressures between the lower surface and the upper surface of each vane 60.
  • the section at the neck 6s between the leading edges 6a is retained .
  • the homogenization of the flow of the air flow F is illustrated in perspective by the figure 6 .
  • a flat flange 90 shown hatched in the figure
  • an aerodynamic blockage is created in the zone Z0 with a very low amount of movement.
  • the main air flow (arrow F) has a high Mach number.
  • the aerodynamic blocking zone is eliminated and the flow of air F is homogenized by occupying the entire passage section offered, with a lower Mach number.
  • the invention is not limited to the embodiments described and shown.
  • the curvatures are alternated in the direction of flow of the fluid F but also in the tangential direction 6t.
  • the zones of alternating curvature can be juxtaposed so that surface portions of the same curvature, hollow or humped, can rub shoulders.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (5)

  1. Diffusionsstufe eines radialen oder gemischten Gasturbinenkompressors, welcher ein Rad (6) umfasst, das aus zwei Flanschen (9) gebildet ist, zwischen denen das Fluid zentrifugal oder geneigt aus der Mitte zur Peripherie strömt, wobei Schaufeln (60) eines Gitters zwischen den Flanschen (9) entlang des Rades (6) verteilt sind, um die Strömung des Fluids zwischen den Vorderkanten (6a) dieser Schaufeln (60) auf Seiten der Mitte, und den Hinterkanten (6f) auf Seiten der Peripherie zu kanalisieren, wobei mindestens einer der Flansche (9) eine Innenseite (9i) aufweist, die mindestens einen Bereich (Z1, Z2) mit abwechselnden vertieften (91) und buckeligen (92) Krümmungen zwischen zwei benachbarten Schaufeln (60) in der Strömungsrichtung entlang der Schaufeln umfasst, und wobei mindestens einer der Flansche (9) eine Innenseite (9i) aufweist, die ebenfalls mindestens einen Bereich (Z1, Z2) mit abwechselnden vertieften (91) und buckeligen (92) Krümmungen zwischen zwei benachbarten Schaufeln (60) in einer tangentialen Richtung zwischen den Schaufeln (6t), im Wesentlichen senkrecht zur Strömungsrichtung entlang der Schaufeln umfasst, dadurch gekennzeichnet, dass sie Vertiefungs- und Buckelbereiche (Z1, Z2) an der Vorderkante (6a) der Schaufeln (60), mit einem Beginn stromaufwärts der Vorderkante (6a) aufweist.
  2. Diffusionsstufe nach Anspruch 1, dadurch gekennzeichnet, dass sie abwechselnde vertiefte (91) und buckelige (92) Bereiche (Z1, Z2) zwischen den Schaufeln, insbesondere bis zu im Wesentlichen 80%, vorzugsweise bis zu im Wesentlichen 50% einer Bogensehne (6c) einer Schaufel (60) aufweist.
  3. Diffusionsstufe an der Vorderkante der Schaufeln nach einem der Ansprüche 1 bis 2, dadurch gekennzeichnet, dass sie Vertiefungs- und Buckelbereiche (Z1, Z2) an der Hinterkante (6f) der Schaufeln (60) bis stromabwärts der Hinterkante (6f) aufweist.
  4. Diffusionsstufe an der Vorderkante der Schaufeln nach einem der Ansprüche 1 bis 3, wobei diese abwechselnden Vertiefungs- und Buckelbereiche (Z1, Z2) auf den einen und/ oder den anderen der beiden Flansche (9) einer zentrifugalen und gemischten Diffusion angewendet werden.
  5. Diffusionsstufe nach dem vorstehenden Anspruch, wobei diese abwechselnden Bereiche (Z1, Z2) auf die Flansche (9) in Bezug auf eine mittlere Symmetrieebene der Flansche (9) symmetrisch oder parallel angewendet werden.
EP12734964.5A 2011-06-20 2012-06-19 Verfahren zum diffundieren einer gasturbinenkompressionsstufe und diffusionsstufe zur durchführung des verfahrens Active EP2721305B1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PL12734964T PL2721305T3 (pl) 2011-06-20 2012-06-19 Sposób dyfuzji dla stopnia sprężania turbiny gazowej i stosowany w tym sposobie stopień dyfuzji

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1155370A FR2976633B1 (fr) 2011-06-20 2011-06-20 Procede de diffusion d'un etage de compression d'une turbine a gaz et etage de diffusion de mise en oeuvre
PCT/FR2012/051367 WO2012175855A1 (fr) 2011-06-20 2012-06-19 Procede de diffusion d'un etage de compression d'une turbine a gaz et etage de diffusion de mise en oeuvre

Publications (2)

Publication Number Publication Date
EP2721305A1 EP2721305A1 (de) 2014-04-23
EP2721305B1 true EP2721305B1 (de) 2021-02-24

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EP12734964.5A Active EP2721305B1 (de) 2011-06-20 2012-06-19 Verfahren zum diffundieren einer gasturbinenkompressionsstufe und diffusionsstufe zur durchführung des verfahrens

Country Status (11)

Country Link
US (1) US20140133957A1 (de)
EP (1) EP2721305B1 (de)
JP (1) JP6261498B2 (de)
KR (1) KR101946084B1 (de)
CN (1) CN103635698B (de)
CA (1) CA2838686C (de)
FR (1) FR2976633B1 (de)
IN (1) IN2014DN00118A (de)
PL (1) PL2721305T3 (de)
RU (1) RU2596691C2 (de)
WO (1) WO2012175855A1 (de)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3003908B1 (fr) 2013-03-28 2017-07-07 Turbomeca Diffuseur a ailettes d un compresseur radial ou mixte
DE102017122524A1 (de) * 2017-09-28 2019-03-28 Abb Turbo Systems Ag Diffusor für einen Verdichter
US11286952B2 (en) 2020-07-14 2022-03-29 Rolls-Royce Corporation Diffusion system configured for use with centrifugal compressor

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20030235497A1 (en) * 2002-06-20 2003-12-25 The Boeing Company Diffuser having a variable blade height

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB685814A (en) * 1950-03-03 1953-01-14 Escher Wyss Ag Improvements in and relating to radial centrifugal compressors and pumps
US6123506A (en) * 1999-01-20 2000-09-26 Pratt & Whitney Canada Corp. Diffuser pipe assembly
RU2197644C1 (ru) * 2001-07-30 2003-01-27 Открытое акционерное общество "Татнефть" Рабочее колесо центробежного насоса
GB0223756D0 (en) * 2002-10-14 2002-11-20 Holset Engineering Co Compressor
RU2330994C2 (ru) * 2006-05-16 2008-08-10 Открытое акционерное общество "Климов" Центробежный компрессор
US8100643B2 (en) * 2009-04-30 2012-01-24 Pratt & Whitney Canada Corp. Centrifugal compressor vane diffuser wall contouring
CN201461538U (zh) * 2009-07-30 2010-05-12 大同北方天力增压技术有限公司 一种抛物线型叶片式扩压器

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20030235497A1 (en) * 2002-06-20 2003-12-25 The Boeing Company Diffuser having a variable blade height

Also Published As

Publication number Publication date
CN103635698B (zh) 2017-06-13
CA2838686C (fr) 2019-09-17
JP2014517217A (ja) 2014-07-17
CN103635698A (zh) 2014-03-12
RU2596691C2 (ru) 2016-09-10
KR20140047653A (ko) 2014-04-22
JP6261498B2 (ja) 2018-01-17
PL2721305T3 (pl) 2021-07-12
IN2014DN00118A (de) 2015-05-22
EP2721305A1 (de) 2014-04-23
FR2976633A1 (fr) 2012-12-21
US20140133957A1 (en) 2014-05-15
KR101946084B1 (ko) 2019-02-08
CA2838686A1 (fr) 2012-12-27
FR2976633B1 (fr) 2015-01-09
RU2013156047A (ru) 2015-07-27
WO2012175855A1 (fr) 2012-12-27

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