EP0719906B1 - Überschallleitschaufel in der Eingangsstufe einer Turbomaschine - Google Patents

Überschallleitschaufel in der Eingangsstufe einer Turbomaschine 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
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English (en)
French (fr)
Other versions
EP0719906A1 (de
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
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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/de
Application granted granted Critical
Publication of EP0719906B1 publication Critical patent/EP0719906B1/de
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)

Claims (13)

  1. Überschallleitschaufel in der Eingangsstufe einer Turbomaschine mit einem Außengehäuse (102), einer Nabe (101), einer Gruppe von Außenschaufeln (103), die ringförmig und aneinandergesetzt an der Nabe (101) angeordnet sind, so daß zwischen den Schaufeln (103) Überschallströmungspassagen (104) erzeugt werden, die eine Strömung mit hohem Druck und kleiner Geschwindigkeit in eine Überschallströmung mit niedrigem Druck transformieren,
    dadurch gekennzeichnet,
    daß die Schaufeln (103) innerhalb eines Strömungsversorgunstorus radial regelmäßig angeordnet sind, daß im Schnitt entlang einer Linie, die einem gegebenen Strahl entspricht, d. h. in einer Ebene von Schaufel zu Schaufel die Schaufeln (103) ein Profil in Form einer zweidimensionalen Halbdüse definieren und daß das Profil einen stromaufwärtigen rechteckigen Abschnitt (134), einen Vorsprung (133), der zum Beschleunigen der Strömung bis auf eine Machzahl von 1 einen Hals (142) definiert, wobei der Hals (142) entlang dem betrachteten Strahl einen variablen Querschnitt aufweist, und einen stromabwärtigen gekrümmten Abschnitt (135) umfaßt, der eine Austrittskante (131) bildet, die senkrecht zur Drehachse abgeschnitten sein kann.
  2. Leitschaufel nach Anspruch 1, dadurch gekennzeichnet, daß die Position des Vorsprungs (133) bei jeder Schaufel (103) und die Länge des stromabwärtigen gekrümmten Abschnitts (135) von dem Verhältnis des gewünschten Druckes beiderseits der Leitschaufel abhängt.
  3. Leitschaufel nach Anspruch 1 oder 2, dadurch gekennzeichnet, daß der Aufbau des Profils der Schaufeln (103) in radialer Richtung durch Beschichten hergestellt wird, wobei das Profil durch Ähnlichkeitstransformation gewonnen wird, die im wesentlichen ein gleiches Verhältnis des betrachteten Strahls zu dem mittleren Strahl der Ader (R) hat.
  4. Leitschaufel nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, daß für jeden Strahl der Austrittswinkel β der Leitschaufel durch eine Verdrillung der Schaufeln (103) zwischen Fuß und Kopf eingestellt wird.
  5. Leitschaufel nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, daß über die gesamte Höhe der Schaufeln (103) eine Abrißkante (131) am Ende wie auch ein Verhältnis zwischen dem Querschnitt des Düsenhalses (104) und dem Austrittsquerschnitt beibehalten wird, das für jeden Strahl in Abhängigkeit von dem gewünschten Druckverhältnis gewählt wird.
  6. Leitschaufel nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, daß die Abrißkante (131) jeder Schaufel (103) zwischen 4 und 8 % des zwischen den aufeinanderfolgenden Schaufeln (103) definierten Schrittes darstellen.
  7. Leitschaufel nach einem der Ansprüche 1 bis 6, dadurch gekennzeichnet, daß die Schaufeln (103) ein sich entlang dem Strahl und frei von eckigen Abschnitten entwickelndes Profil aufweisen.
  8. Leitschaufel nach einem der Ansprüche 1 bis 7, dadurch gekennzeichnet, daß die Schaufeln (103) getrennt und mit Bezug auf die Nabe (101) hergestellt werden.
  9. Leitschaufel nach einem der Ansprüche 1 bis 8, dadurch gekennzeichnet, daß die Schaufeln (103) in der Nabe (101) und dem Außengehäuse (102) durch Teile in Form eines Tannenfußes verankert sind.
  10. Leitschaufel nach Anspruch 8 oder 9, dadurch gekennzeichnet, daß sie mit pulvermetallurgischer Technik hergestellt wird.
  11. Leitschaufel nach einem der Ansprüche 1 bis 10, dadurch gekennzeichnet, daß die Schaufeln (103) derart ausgelegt sind, daß sie am Ausgang einen Überschallstrom zwischen Mach 1,2 und Mach 2,5 erzeugen.
  12. Leitschaufel nach einem der Ansprüche 1 bis 11, dadurch gekennzeichnet, daß sie für eine Turbopumpenturbine ausgelegt ist.
  13. Leitschaufel nach Anspruch 12, dadurch gekennzeichnet, daß die Schaufeln am Ausgang eine Neigung zwischen 65° und 80° in bezug auf die Achse der Leitschaufel einhalten.
EP95402940A 1994-12-27 1995-12-26 Überschallleitschaufel in der Eingangsstufe einer Turbomaschine Expired - Lifetime EP0719906B1 (de)

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 (de) 1996-07-03
EP0719906B1 true EP0719906B1 (de) 1999-04-14

Family

ID=9470273

Family Applications (1)

Application Number Title Priority Date Filing Date
EP95402940A Expired - Lifetime EP0719906B1 (de) 1994-12-27 1995-12-26 Überschallleitschaufel in der Eingangsstufe einer Turbomaschine

Country Status (6)

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

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US6508631B1 (en) 1999-11-18 2003-01-21 Mks Instruments, Inc. Radial flow turbomolecular vacuum pump
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WO2002004788A1 (en) * 2000-07-06 2002-01-17 Drysdale Kenneth William Patte Turbine, power generation system therefor and method of power generation
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
CN102869880A (zh) * 2010-03-19 2013-01-09 Sp技术公司 推进器叶片
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
JP6025961B2 (ja) * 2013-02-21 2016-11-16 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
WO2019167319A1 (ja) 2018-02-27 2019-09-06 株式会社Ihi ロケットエンジン用ターボポンプ
EP3569817B1 (de) * 2018-05-14 2020-10-14 ArianeGroup GmbH Leitschaufelanordnung zur verwendung in einer 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

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Also Published As

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

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