US20130034425A1 - Method for adapting the air flow of a turbine engine having a centrifugal compressor and diffuser for implementing same - Google Patents

Method for adapting the air flow of a turbine engine having a centrifugal compressor and diffuser for implementing same Download PDF

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Publication number
US20130034425A1
US20130034425A1 US13/640,978 US201113640978A US2013034425A1 US 20130034425 A1 US20130034425 A1 US 20130034425A1 US 201113640978 A US201113640978 A US 201113640978A US 2013034425 A1 US2013034425 A1 US 2013034425A1
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US
United States
Prior art keywords
blade
blades
blade ring
diffuser
variable pitch
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.)
Abandoned
Application number
US13/640,978
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English (en)
Inventor
Pierre Biscay
Patrick Marconi
Hubert Hippolyte Vignau
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
Original Assignee
Turbomeca SA
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Filing date
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Application filed by Turbomeca SA filed Critical Turbomeca SA
Assigned to TURBOMECA reassignment TURBOMECA ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: BISCAY, PIERRE, MARCONI, PATRICK, VIGNAU, HUBERT HIPPOLYTE
Publication of US20130034425A1 publication Critical patent/US20130034425A1/en
Assigned to SAFRAN HELICOPTER ENGINES reassignment SAFRAN HELICOPTER ENGINES CHANGE OF NAME (SEE DOCUMENT FOR DETAILS). Assignors: TURBOMECA
Abandoned legal-status Critical Current

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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
    • F04D29/40—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
    • 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
    • F04D29/46—Fluid-guiding means, e.g. diffusers adjustable
    • 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
    • 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 an adaptation method for the air flow rate in a turbine engine, comprising a centrifugal compressor, in particular of a turbine engine of helicopters or auxiliary power units (in short APU) to a variable demand for flow rate or mechanical or electrical power.
  • the invention also relates to a diffuser equipped with variable pitch blades for implementing such method.
  • the scope of the invention is gas compression in turbine engines and more particularly the adaptation of the compressed air flow to take the engine performances into account, whatever these are turbine engines or APUs, in particular the specific consumption (in short Cs) thereof under partial load.
  • variable pitch is obtained with appropriate controls in relationship with a control unit depending on the physical parameters at issue (rotation speed, pressures, temperatures).
  • pitch angle ranges that the control system must cover need a control jack of high power lead to important variations of the inlet and outlet diameters of the diffuser, which can generate high mechanical biases between rotating parts (sheave) and static parts (radial variable pitch diffuser) and reduces yield under partial load (intermediate rating).
  • the invention aims at obviating such drawbacks, in particular by maintaining the compressor yield to substantially reduce the Cs while providing a sufficient pumping margin with a better yield of the motive cycle under partial load. To do so, it proposes an optimized method for a variable diffusion of the air flow in a centrifugal compressor of turbine engines.
  • the invention has for an object a method for a variable diffusion of the air flow in a centrifugal compressor of turbine engines, consisting in providing a diffusion of the air through a first annular blade ring with variable pitch blades, radially bordered with a second annular blade ring having the same number of fixed pitch blades with an equivalent extension, guiding the diffusion in the radial direction by coupling the blades of the two blade rings, each blade of the first blade ring being driven into rotation at distance of the blade.
  • turbine engines means the turbine engines, in particular those of helicopters with a centrifugal mono- or bi-staged compressor, and the APUs equipped with a centrifugal mono- or bi-staged centrifugal compressor.
  • variable pitch blades on the one side, the radial extension of the variable pitch blades is substantially reduced by the presence of the fixed blade ring comprising real blades, thereby allowing to limit the stresses to vary their pitch as well as the clearances between the fixed blade ring and the support flange and, thus, the upstream/downstream re-circulations, thereby having as an effect to reduce the pumping line deteriorations and the load losses.
  • the off-axis implantation of the rotation axis of the variable pitch blades substantially reduces the radial extension variations for such iso-diffusion blades: the closing increase is lesser, thereby favouring the yield under partial load and the opening decrease also lesser, thereby limiting the mechanical biases due to the non stationary aerodynamic fluctuations by a sheave/diffuser interaction.
  • a sufficient pumping margin then allows the turbine engine to operate with any appearance of pumping—providing a great acceleration capacity—, and the APUs to face important load variations without calling on a discharge valve, while maintaining the rotation speed of the turbine engine and the pressure rate thereof at levels close to their nominal values and providing a sufficient yield level.
  • the method applying to turbine engines equipped with a power turbine, the variable pitch radial diffusion on a centrifugal compressor, such as defined above, is coupled with a variable pitch power turbine distributor.
  • the power production can be implemented according to several configurations: free or bound power turbine, of the axial or centripetal type, with or without downstream heat exchange.
  • the coupling between the diffuser and the variable pitch distributor allows the operation line to be adapted to the flow rate reduction, thereby improving the motive cycle yield (through a better pressure rate) and thus the Cs of the turbine engines of helicopters and APUs.
  • the invention also aims at providing a variable pitch turbine engine diffuser being able to implement the above mentioned method, as well as the turbine engine equipped with such a diffuser.
  • the diffuser comprises a first annular blade ring with variable pitch blades being radially bordered by a second annular blade ring with fixed pitch blades of an equivalent extension.
  • each blade of the first blade ring is driven by control means adapted to exert a proper rotation of each blade being off-centered with respect to the rotation axis thereof.
  • each variable pitch blade extends between two facing cups and in a parallel and off-axis way with respect to the common axis of the cups coinciding with the rotation axis;
  • each blade is coupled with a driving rod that presents at least one orifice in which a lock pin is introduced for an adjustment washer for the axial position of the cups;
  • the rod is integral with a lever presenting a ball joint coupling housed within a cylindrical housing ( 38 ) of a control crown adapted to drive into rotation around the motive axis the lever being adapted to slide in the cylindrical housing;
  • the cylindrical housings present a depth being a function of the stroke of the levers, itself a function of the predetermined rotation interval of the blades;
  • each variable pitch blade is close to the peripheries of the cups, the distance from the blade to the rotation axis being higher than or equal to a mid-radius;
  • the diffuser upstream is a smooth diffuser, i.e. with no vane
  • the inlet air stream of the diffuser located between the sheave and the variable pitch blade ring is convergent, thereby improving the performances
  • the fixed blades of the second blade ring present a thicker leading edge profile than the ones of the first blade ring so as to absorb the incidence variations
  • the fixed pitch blades present a sufficient thickness to be crossed by screws allowing the passage of structural stresses
  • the fixed blades present a skeleton angle evolution law between the leading and trailing edges, thereby allowing the diffusion in the fixed blade ring to be controlled and the aerodynamic efficiency to be optimized;
  • the fixed blades are keyed in azimuth with respect to the blades of the first mobile blade ring so as to take the wake again on the suction side of the blades in the first blade ring so as to limit the load losses of the diffuser;
  • the pitch angles of the variable blades are comprised between +12° and ⁇ 5° with respect to the nominal keying, which could be the one of a fixed diffuser.
  • FIG. 1 represents half a view in an axial partial section of a diffuser according to the invention
  • FIGS. 2 a and 2 b represents two views in perspective of a variable pitch blade coupled to the control rod thereof in rotation;
  • FIG. 3 represents a front global view of the upstream annular flange of the diffuser equipped with blade rings according to the invention
  • FIGS. 4 a to 4 c represent a partial schematic view in the diffuser for three mobile blade pitches, the two extreme pitches around the nominal pitch, and
  • FIG. 5 represents the clearance between a mobile blade and the annular flanges of the diffuser.
  • upstream and downstream relate to the air flow direction in a turbine engine.
  • the centrifugal compressor 10 of a turbine engine such as a turbomachine, a turbine reactor jet, a turbine propeller or an APU, comprises a casing 12 coupled with a cover 14 for radially covering the sheave 16 , the last centrifugal stage of the compressor, rotationally mounted on the motive shaft 18 according to the axis Y′Y.
  • the airflow F circulates from the sheave 16 toward the annular diffuser 19 in an inlet stream converging by radial a narrowing.
  • the diffuser 19 is defined between two upstream and downstream flanges 20 and 22 .
  • the cover 14 is maintained by an attachment 23 fastened to the casing and to the upstream flange 20 .
  • the blades 24 forming a first annular blade ring are mounted in the diffuser 19 .
  • Centerings 25 and 26 are facing the flanges 20 and 22 accommodating the cups 17 and 27 on which the blades 24 are mounted on an off-axis way.
  • the cups are centered in the flanges 20 and 22 with adapted clearances, from 0.03 to 0.05 mm in the illustrated examples on a washer 9 inserted into the centering 25 (see below referring to FIG. 5 ).
  • Blades 28 being integral with the flange 22 , forming a second annular blade ring externally bordering the first blade ring, are mounted on the annular flange 20 by screws 29 housed in through-holes 29 t. These screws also admit the passage of structural stresses.
  • the control of the variable blades 24 is made through rods 30 extending integrally the upstream cup 17 .
  • These rods 30 with an axis X′X are mounted in a cylindrical boring 32 of the upstream flange 20 and centered with a quasi null clearance by joints 30 j mounted in grooves 30 g.
  • each rod 30 presents a flat part 31 jointed on a driving lever 33 pinched by two screws 35 on such flat part 31 .
  • the positions of the ends 31 of the rods 30 are adjusted with adapted clearance tolerances.
  • the rod 30 also presents an orifice 30 t into which a pin 36 is inserted so as to lock a washer 30 u —for adjusting the axial position of the cups 17 and 27 —in an locking ring 12 a being formed in the casing 12 .
  • the pin 36 makes the rod 30 and the locking ring 12 a integral.
  • the lever 33 is driven by a control crown 34 forming a cylindrical hole 38 for housing the ball joint coupling 37 of the lever 33 with an adapted axial position tolerance and a contact on a generatrix of the ball joint.
  • the control crown 34 is centered on sectors presenting needle roller bearings 39 .
  • the control crown 34 put into rotation around the motive axis Y′Y by a rocker bar (not shown) drives into rotation the levers 33 sliding in the cylindrical housings 38 thanks to their ball joint 37 .
  • the depth of the housings 38 depends on the stroke of the lever 33 , itself being a function of the rotation interval of the blades 24 .
  • Such architecture is particularly adapted for a blade rotation being able to go up to +12° with a section closure of 50% section and up to ⁇ 5° with a section opening of 20%.
  • the position angles of the rods and thus of the blades 24 are a function of the power rates to provide the adequate air compression to these ratings.
  • a mobile blade 24 is represented between the parallel cups 17 , 27 and integral with the latter by welding 21 , so that the blade extends parallel to the axis X′X of the facing cups.
  • the leading edge 24 c of the blade 24 is flush with the external circumferences 17 c and 27 c of the cups, the thickness of the blade 24 being quite fine, about 2 mm in the illustrated example.
  • the distance between the blade 24 and the axis X′X of the rod 30 is equal to about 80% of the radius of the cups in the illustrated example. This confers to the blade 24 a strong off-centering with respect to the axis X′X of the rod coinciding with the rotation axis of the assembly.
  • the rod 30 also presents the cylindrical centering grooves 30 g and the locking orifice 30 t for the adjustment washer of the axial position of the cups 17 and 27 .
  • the flat part 31 thereof is crossed by reception holes 30 a for the screws 35 used for mounting the control lever.
  • FIG. 3 illustrates the upstream annular flange 20 equipped with annular blade rings G 1 and G 2 being respectively mounted mobile and fixed and formed with the blades 24 and 28 .
  • the blades 28 present a substantially thicker profile in the leading edge BA than the one of the blades 24 , respectively 0.5 and 2.5 mm, so as to keep a good behavior to the incidence variation upon the rotation of the mobile blades 24 .
  • the skeleton angle law of the blades 28 between the leading and trailing edges BA and BF is evolutive, thereby allowing the aerodynamic efficiency of the fixed blade ring to be optimized by a maximum recovery of the static pressure.
  • the blades 28 of the fixed blade ring present a maximum thickness of 7 mm in the illustrated example, allowing the flange 20 of the diffuser to be fastened by screws housed in the holes 29 t, while admitting the passage of structural stresses.
  • the airflow F circulates along a fixed blade 28 in a radial extension of a mobile blade 24 and between two adjacent blades of the same nature, either mobile or fixed. Thanks to the off-centering of the mobile blades 24 with respect to the rotation axes X′X of their cups 17 , the variations of the radial extensions formed by such mobile blades 24 are limited relative to the extension variation that the centered blade should implement. This limitation enables to improve the performances of a centrifugal compressor: it allows the operation lines of the pumping line to be more distant by an offset towards lower flow rates, and this line of operation to be increased near the yield maximums at higher ratings.
  • FIGS. 4 a to 4 c The radial extensions of the mobile blades 24 facing the fixed blades 28 are illustrated by the schemas of FIGS. 4 a to 4 c , on which also appear, in dot lines, the cups 17 , 27 of the blades.
  • the nominal keying of 0° corresponds to a reference airflow stream F for which the adjustment of the mobile blades 24 with respect to the fixed blades 28 is adapted to the stable intermediate ratings.
  • the keying of the mobile blades 24 may rise up to 12°, this keying corresponding to a passage section at the inlet of the collar Sa, between the blades 24 and 38 , closed at 50% with respect to the nominal keying corresponding to a section at the collar Sb.
  • FIG. 4 a illustrates the case of a closure of 25% associated with a keying of 6°, the collar section being then 75% of the section b.
  • the keying adjustment may also go down to ⁇ 5°.
  • FIG. 4 c illustrates the case of an opening of 2.5°, the collar section Se presenting then a relative value of 110%.
  • the fixed blades 28 are keyed in azimuth with respect to the blades 24 of the first mobile blade ring G 1 so as to take again the wake on the suction side Ex of the blades of this first blade ring G 1 .
  • the radial extensions of the blades 24 limited by the presence of the fixed blades 28 allow a control to be kept on the clearances between the cups 17 and 27 of the blades 24 and the flanges 20 and 22 , as illustrated by FIG. 5 .
  • the clearance values stay lower than or equal respectively to 0.02 mm (for J 1 or J 2 ), 0.10 mm (for J 3 ) and 0.25 mm (for J 4 ).
  • the clearance (J 1 and J 2 assembly) of the blade 24 on the washer 9 thus stays of about 0.03 mm of slightly more.
  • the invention is not limited to the example being described and represented. It is for example possible to perform the keying of the mobile blades only by a mechanical, individual or centralized, adjustment or by an electrical or electronic control with or without digital regulation.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US13/640,978 2010-04-14 2011-04-13 Method for adapting the air flow of a turbine engine having a centrifugal compressor and diffuser for implementing same Abandoned US20130034425A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR1052827A FR2958967B1 (fr) 2010-04-14 2010-04-14 Procede d'adaptation de debit d'air de turbomachine a compresseur centrifuge et diffuseur de mise en oeuvre
FR1052827 2010-04-14
PCT/FR2011/050846 WO2011128587A1 (fr) 2010-04-14 2011-04-13 Procédé d'adaptation de débit d'air de turbomachine à compresseur centrifuge et diffuseur de mise en oeuvre

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US20130034425A1 true US20130034425A1 (en) 2013-02-07

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US (1) US20130034425A1 (fr)
EP (1) EP2558728B2 (fr)
JP (2) JP2013524099A (fr)
KR (1) KR20130079326A (fr)
CN (1) CN102834622B (fr)
CA (1) CA2794825C (fr)
FR (1) FR2958967B1 (fr)
PL (1) PL2558728T5 (fr)
RU (1) RU2564158C2 (fr)
WO (1) WO2011128587A1 (fr)

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US11105338B2 (en) 2016-05-26 2021-08-31 Rolls-Royce Corporation Impeller shroud with slidable coupling for clearance control in a centrifugal compressor
US11177489B2 (en) * 2017-11-01 2021-11-16 Ihi Corporation Centrifugal compressor with diffuser
US11466592B2 (en) * 2018-09-04 2022-10-11 Siemens Energy Global GmbH & Co. KG Turbomachine housing having at least one cover, turbomachine, method for producing a cover

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CN103925246B (zh) * 2013-01-11 2017-06-09 哈米尔顿森德斯特兰德公司 用于空气循环机的压缩机壳体
JP2014152637A (ja) * 2013-02-05 2014-08-25 Mitsubishi Heavy Ind Ltd 遠心圧縮機
FR3003908B1 (fr) * 2013-03-28 2017-07-07 Turbomeca Diffuseur a ailettes d un compresseur radial ou mixte
GB2513666B (en) * 2013-05-03 2015-07-15 Dyson Technology Ltd Compressor
BE1025194B1 (fr) * 2017-05-05 2018-12-07 Safran Aero Boosters S.A. Capteur de turbulences dans un compresseur de turbomachine
CN112983846A (zh) 2019-12-02 2021-06-18 开利公司 离心压缩机和运行离心压缩机的方法

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RU2012148378A (ru) 2014-05-20
JP6483074B2 (ja) 2019-03-13
WO2011128587A1 (fr) 2011-10-20
CN102834622A (zh) 2012-12-19
FR2958967A1 (fr) 2011-10-21
EP2558728B1 (fr) 2019-07-24
JP2017061936A (ja) 2017-03-30
FR2958967B1 (fr) 2013-03-15
RU2564158C2 (ru) 2015-09-27
JP2013524099A (ja) 2013-06-17
CN102834622B (zh) 2016-02-10

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