EP0719906B1 - Distributeur supersonique d'étage d'entrée de turbomachine - Google Patents

Distributeur supersonique d'étage d'entrée de turbomachine Download PDF

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Publication number
EP0719906B1
EP0719906B1 EP95402940A EP95402940A EP0719906B1 EP 0719906 B1 EP0719906 B1 EP 0719906B1 EP 95402940 A EP95402940 A EP 95402940A EP 95402940 A EP95402940 A EP 95402940A EP 0719906 B1 EP0719906 B1 EP 0719906B1
Authority
EP
European Patent Office
Prior art keywords
blades
distributor
distributor according
radius
profile
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.)
Expired - Lifetime
Application number
EP95402940A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0719906A1 (fr
Inventor
Frédéric Pommel
Andréas von Kaenel
Jacques Desclaux
Georges Meauze
Gilles M. Billonnet
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 Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
SNECMA SAS
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 Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0719906A1 publication Critical patent/EP0719906A1/fr
Application granted granted Critical
Publication of EP0719906B1 publication Critical patent/EP0719906B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • 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
    • 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
    • F05D2240/302—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor characteristics related to shock waves, transonic or supersonic flow

Definitions

  • the construction of the profile of the blades in the radial direction is carried out by stacking while respecting a homothety of the profile substantially equal to the ratio of the radius considered to the mean radius of the vein.
  • the distributor outlet angle is adjusted by a twisting of the blades between the foot and the head.
  • the ratio between the section of the nozzle neck and the outlet section is chosen at each radius according to the desired pressure ratio so as to comply with a law of radial balance.
  • the trailing edge of each blade represents from 4 to 8% of the pitch defined between the successive blades.
  • the blades have an evolving profile according to the radius and free of parts angular, with the exception of trailing edges and leading edges which may be advantageously truncated.
  • the blades are manufactured separately and attached to the hub.
  • the blades are anchored in the hub and the outer casing by parts in the shape of a fir tree base.
  • the dispenser according to the invention can be produced according to the technology of the powder metallurgy.
  • the blades are adapted to define at the outlet a supersonic flow between Mach 1.2 and Mach 2.5.
  • the distributor according to the invention is particularly suitable for a turbine turbopump.
  • the blades have an inclination at output between 65 and 80 ° relative to the axis of the distributor.
  • the geometry of the distributor according to the invention makes it possible to obtain a supersonic output speed while respecting radial balance and ensuring a complete supply of the vein at the inlet of the first rotor.
  • FIG. 1 the overview of a supersonic distributor 110 according to the invention comprising a set of vanes 103 distributed between a hub 101 and an outer casing 102.
  • Figures 2 to 5 show the fluid passages 104 formed between the vanes 103 whose leading edge and trailing edge respectively carry the references 132 and 131.
  • the vanes 103 In section developed according to a given radius; for example in cross section of foot (Figure 2), in medium section ( Figure 3) and in head section (Figure 4), the vanes 103 define a profile in the form of a two-dimensional half-nozzle.
  • each dawn 103 in a dawn to dawn plan such as those of Figures 2 to 4
  • has a straight upstream portion 134, a boss 133 defining a neck 142 to accelerate the flow to Mach 1, and a curved downstream part 135 which ends in a uniform flow region with a trailing edge 131 end which can be truncated perpendicular to the axis of rotation.
  • the profile of the distributor blades 110 according to the invention is characterized in particular by the presence of a leading edge 132 end and especially a trailing edge 131 end.
  • the thickness e of the trailing edge 131 can be between approximately 4 and 8% of the pitch p defined between the successive vanes 103 (FIG. 3).
  • a thickness e of the trailing edge 131 of the order of 6% of the pitch p is generally satisfactory for limiting the level of losses and improving the quality of the flow.
  • the construction of the profile of a blade 103 in the radial direction of the height H of dawn is performed by stacking while respecting a profile homothety substantially equal to the ratio of the radius considered to the average radius R of the vein.
  • the distributor outlet angle is adjusted by a twisting of the blades 103 between the foot 101 and the head 102. This is done so as to allow a respect of the radial evolution of the Mach triangle at the entry of the wheel mobile.
  • the changing profile of the blades 103 is such that the blades are free of angular parts with the exception of leading edges and edges which can advantageously be truncated.
  • the vanes 103 can be manufactured separately and attached to the hub 101.
  • the blades 103 can be anchored in the hub 101 and the outer casing 102 by ends 138, 139 in the shape of a fir tree foot.
  • a vane distributor according to the invention can advantageously be produced according to powder metallurgy technology.
  • the vanes 103 may have various inclinations at the outlet according to the applications envisaged.
  • the tilt vanes 103 relative to the axis of the distributor can be between approximately 65 and 80 °.
  • Figure 7 concerns the previous example and shows the triangles of speeds upstream of the turbine rotor at foot level (vectors A, A '), a mean radius (vectors B, B ') and of the head (vectors C, C').
  • Vectors A, B, C give the output speed values in number of Mach (namely 1.86; 1.74 and 1.63 respectively) for an absolute inclination ⁇ a 74 °, for the foot, at the medium radius and the head of the blades 103.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP95402940A 1994-12-27 1995-12-26 Distributeur supersonique d'étage d'entrée de turbomachine Expired - Lifetime EP0719906B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9415693 1994-12-27
FR9415693A FR2728618B1 (fr) 1994-12-27 1994-12-27 Distributeur supersonique d'etage d'entree de turbomachine

Publications (2)

Publication Number Publication Date
EP0719906A1 EP0719906A1 (fr) 1996-07-03
EP0719906B1 true EP0719906B1 (fr) 1999-04-14

Family

ID=9470273

Family Applications (1)

Application Number Title Priority Date Filing Date
EP95402940A Expired - Lifetime EP0719906B1 (fr) 1994-12-27 1995-12-26 Distributeur supersonique d'étage d'entrée de turbomachine

Country Status (6)

Country Link
US (1) US5676522A (enExample)
EP (1) EP0719906B1 (enExample)
JP (1) JP3779360B2 (enExample)
CA (1) CA2165863A1 (enExample)
DE (1) DE69509056T2 (enExample)
FR (1) FR2728618B1 (enExample)

Families Citing this family (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6508631B1 (en) 1999-11-18 2003-01-21 Mks Instruments, Inc. Radial flow turbomolecular vacuum pump
US6358012B1 (en) 2000-05-01 2002-03-19 United Technologies Corporation High efficiency turbomachinery blade
WO2002004788A1 (en) * 2000-07-06 2002-01-17 Drysdale Kenneth William Patte Turbine, power generation system therefor and method of power generation
RU2202696C2 (ru) * 2001-02-22 2003-04-20 Масютин Владимир Ильич Газотурбинный двигатель
US7334990B2 (en) * 2002-01-29 2008-02-26 Ramgen Power Systems, Inc. Supersonic compressor
US20030210980A1 (en) * 2002-01-29 2003-11-13 Ramgen Power Systems, Inc. Supersonic compressor
US7293955B2 (en) * 2002-09-26 2007-11-13 Ramgen Power Systrms, Inc. Supersonic gas compressor
US7434400B2 (en) * 2002-09-26 2008-10-14 Lawlor Shawn P Gas turbine power plant with supersonic shock compression ramps
GB0323909D0 (en) * 2003-10-11 2003-11-12 Rolls Royce Plc Turbine blades
FR2868467B1 (fr) * 2004-04-05 2006-06-02 Snecma Moteurs Sa Carter de turbine a crochets refractaires obtenu par procede mdp
DE102009013399A1 (de) † 2009-03-16 2010-09-23 Mtu Aero Engines Gmbh Tandemschaufelkonstruktion
EP2547904B1 (en) * 2010-03-19 2019-05-08 SP Tech Propeller blade
US8683791B2 (en) 2010-08-20 2014-04-01 Toyota Motor Engineering & Manufacturing North America, Inc. Method and system for homogenizing exhaust from an engine
JP6030853B2 (ja) * 2011-06-29 2016-11-24 三菱日立パワーシステムズ株式会社 タービン動翼及び軸流タービン
WO2014128898A1 (ja) * 2013-02-21 2014-08-28 三菱重工業株式会社 タービン動翼
CN104420888B (zh) * 2013-08-19 2016-04-20 中国科学院工程热物理研究所 渐缩流道跨音速涡轮叶片及应用其的涡轮
CN105822432A (zh) * 2016-04-22 2016-08-03 山东元动力科技有限公司 一种微型涡喷发动机
US10677077B2 (en) 2017-03-01 2020-06-09 Panasonic Corporation Turbine nozzle and radial turbine including the same
CN107023395B (zh) * 2017-06-07 2019-02-26 中国空气动力研究与发展中心计算空气动力研究所 一种可调喉道面积的超声速飞行器进气道及调节方法
US10710705B2 (en) 2017-06-28 2020-07-14 General Electric Company Open rotor and airfoil therefor
CN107489462A (zh) * 2017-09-18 2017-12-19 中国船舶重工集团公司第七0四研究所 涡轮机用沿流线周向扩张的扇形截面超音速喷嘴
JP6841376B2 (ja) * 2018-02-27 2021-03-10 株式会社Ihi ロケットエンジン用ターボポンプ
EP3569817B1 (en) * 2018-05-14 2020-10-14 ArianeGroup GmbH Guide vane arrangement for use in a turbine
CN111425259A (zh) * 2020-02-27 2020-07-17 合肥通用机械研究院有限公司 一种磁悬浮超音速透平膨胀机
US11840939B1 (en) * 2022-06-08 2023-12-12 General Electric Company Gas turbine engine with an airfoil
US12066027B2 (en) 2022-08-11 2024-08-20 Next Gen Compression Llc Variable geometry supersonic compressor
WO2024035894A1 (en) 2022-08-11 2024-02-15 Next Gen Compression Llc Method for efficient part load compressor operation

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NL4075C (enExample) * 1913-10-31
US1801427A (en) * 1927-03-12 1931-04-21 Holzwarth Gas Turbine Co Gas-turbine blade
US3156407A (en) * 1958-07-07 1964-11-10 Commissariat Energie Atomique Supersonic compressors
US3333817A (en) * 1965-04-01 1967-08-01 Bbc Brown Boveri & Cie Blading structure for axial flow turbo-machines
CH427851A (de) * 1965-04-01 1967-01-15 Bbc Brown Boveri & Cie Laufschaufelkranz für transsonische Strömung
US3565548A (en) * 1969-01-24 1971-02-23 Gen Electric Transonic buckets for axial flow turbines
US4408957A (en) * 1972-02-22 1983-10-11 General Motors Corporation Supersonic blading
GB1420318A (en) * 1972-11-04 1976-01-07 Rolls Royce Method and apparatus for manufaccturing an article from a particulate material
US4639189A (en) * 1984-02-27 1987-01-27 Rockwell International Corporation Hollow, thermally-conditioned, turbine stator nozzle
US4968216A (en) * 1984-10-12 1990-11-06 The Boeing Company Two-stage fluid driven turbine
US5277549A (en) * 1992-03-16 1994-01-11 Westinghouse Electric Corp. Controlled reaction L-2R steam turbine blade

Also Published As

Publication number Publication date
JP3779360B2 (ja) 2006-05-24
CA2165863A1 (en) 1996-06-28
JPH08232603A (ja) 1996-09-10
FR2728618A1 (fr) 1996-06-28
US5676522A (en) 1997-10-14
EP0719906A1 (fr) 1996-07-03
DE69509056T2 (de) 1999-10-21
DE69509056D1 (de) 1999-05-20
FR2728618B1 (fr) 1997-03-14

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