EP0719906A1 - Leitschaufelform für Überschallbereich in der ersten Stufe einer Turbomaschine - Google Patents

Leitschaufelform für Überschallbereich in der ersten Stufe einer Turbomaschine Download PDF

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Publication number
EP0719906A1
EP0719906A1 EP95402940A EP95402940A EP0719906A1 EP 0719906 A1 EP0719906 A1 EP 0719906A1 EP 95402940 A EP95402940 A EP 95402940A EP 95402940 A EP95402940 A EP 95402940A EP 0719906 A1 EP0719906 A1 EP 0719906A1
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EP
European Patent Office
Prior art keywords
blades
distributor
radius
supersonic
flow
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
EP95402940A
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English (en)
French (fr)
Other versions
EP0719906B1 (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
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Societe Europeenne de Propulsion SEP SA
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Publication of EP0719906A1 publication Critical patent/EP0719906A1/de
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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 present invention relates to the field of turbomachinery and more particularly supersonic turbines.
  • Document FR-A-2 560 287 thus shows an example of a rocket engine turbopump turbine distributor.
  • a fixed annular stator distributor or nozzle comprises a number of fins having a spacing and a configuration such that they distribute and direct the gas flow in the desired manner towards the blades.
  • each fin has a hollow core in order to reduce thermal stresses and can be made of injection molded ceramic or of injection molded refractory metal, cast or machined.
  • Each fin has external and internal horn-shaped plates to which the body of the fin is attached.
  • a floating support device for the fins is intended to allow each fin to be adjusted relative to the direction of the flow of fluid.
  • Such an arrangement is complex to produce and has a geometry which causes significant stresses on the fins.
  • supersonic vane distributors of the first stage of a turbopump turbine in particular for pumping propellants of rocket motors, which are produced in a single block and are intended to transform a flow at high pressure and low speed into a flow supersonic at high speed and strong tangential component to power the first mobile wheel of the turbine.
  • the blades of the distributor constitute a series of two-dimensional supersonic nozzles machined in the mass and distributed periodically according to a ring in planes tangents to the average meridian surface of the cylindrical vein.
  • FIGS. 8 to 11 of the appended drawings An example of such a conventional paddle supersonic distributor is illustrated in FIGS. 8 to 11 of the appended drawings.
  • FIG. 8 shows the configuration of such a conventional distributor 10 in the outlet plane.
  • a tear-off makes it possible to see the ends 31 of the blades 3 close of the outlet plane, which are attached to the hub 1 and to the external casing 2 by enlarged parts 312, 313.
  • FIG. 9 shows an enlarged section along line IX-IX of Figure 8, in a tangential plane of the distributor.
  • FIG. 9 shows the shape of the passage channel of a two-dimensional elementary nozzle 4 with a divergent part 43.
  • Figure 10 illustrates in perspective a portion of the dispenser of Figure 8 and Figure 11 corresponds to a section of the portion shown in Figure 10, in an area near the trailing edge.
  • a blade 3 has a central portion 311 attached to the hub 1 and the outer casing 2 by portions 312, 313 creating sudden variations in thickness in which the mechanical stresses symbolized by the arrows 314 and 315 accumulate.
  • a dispenser such as that illustrated in Figures 8 to 11 has a number of drawbacks.
  • the outlet flow is tangential and does not include a gyration compatible with the radial equilibrium which it is sought to obtain upstream of the moving wheel.
  • This tangential flow strikes the outer casing of the movable wheel and generates shock waves, likely to cause risks of detachment at the inlet of the movable wheel.
  • a tangential vane distributor such as that which has been described has thick three-dimensional trailing edges and steps between the side walls of the individual nozzles and the casings of the moving wheel. There are thus strong distortions of the flow in the radial and azimuthal direction. In particular, there has been a significant deterioration in the stop pressure averaged azimuthally near the outer casing, this degradation revealing the presence of detachment at the outer casing.
  • the object of the present invention is to remedy the drawbacks of bladed supersonic distributors of the prior art and in particular to make it possible to obtain a supersonic speed at the outlet of the distributor while respecting a law of radial balance at the inlet of the first turbine rotor so as to ensure a good speed profile over the entire height of the blades.
  • a supersonic distributor of a turbomachine inlet stage comprising an outer casing, a hub, a set of peripheral vanes arranged in a ring and attached to the hub to provide fluid passages between the vanes.
  • the vanes are arranged radially in a regular manner within a toroid of fluid supply, in that, in section developed according to a line corresponding to a given radius, that is to say in a blade-to-blade plane, the blades define a profile in the form of a two-dimensional half-nozzle and in that said profile has a straight upstream part, a boss defining a neck to accelerate the flow up to a Mach number equal to 1, the neck having a variable section according to the radius considered, and a downstream courtyard part be which ends in a uniform flow region with a trailing edge which can be truncated perpendicular to the axis of rotation.
  • the position of the boss of each blade and the length of the curved downstream part are defined as a function of the desired pressure ratio on either side of the distributor.
  • 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 twist 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 as a function of the desired pressure ratio so as to comply with a radial equilibrium law.
  • 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 along the radius and free of angular parts, with the exception of the trailing edges and the leading edges which can advantageously be 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 powder metallurgy.
  • the vanes are adapted to define at the output a supersonic flow comprised between Mach 1.2 and Mach 2.5.
  • the distributor according to the invention is particularly suitable for a turbopump turbine.
  • the blades have an inclination at output of 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 speed at the outlet while respecting the radial equilibrium and ensuring a complete supply of the vein at the inlet of the first rotor.
  • the greater structural regularity of the blades of a distributor according to the invention is also very advantageous insofar as it results in the abrupt abrupt variations in thickness favorable to the accumulation of stresses.
  • FIG. 1 shows the overall view of a supersonic distributor 110 according to the invention comprising a set of vanes 103 distributed between a hub 101 and an external casing 102.
  • vanes 103 are arranged radially in a regular fashion, in a crown, within a fluid supply torus.
  • FIGS. 2 to 5 show the fluid passages 104 formed between the vanes 103, the leading edge and the trailing edge of which bear the references 132 and 131 respectively.
  • the blades 103 In section developed according to a given radius; for example in cross section (Figure 2), in medium section ( Figure 3) and in head section (Figure 4), the blades 103 define a profile in the form of a two-dimensional half-nozzle.
  • the position of the bosses 133 defining the necks 142 of the nozzles, as well as the length of the downstream sections 135 of the blades 103 are defined as a function of the desired pressure ratio on either side of the distributor.
  • 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 to limit the level of losses and improve the quality of the flow.
  • the construction of the profile of a blade 103 in the radial direction of the height H of the blade is achieved by stacking while respecting a profile uniformity substantially equal to the ratio of the radius considered to the mean radius R of the vein.
  • the distributor outlet angle is adjusted by a twist of the vanes 103 between the foot 101 and the head 102. This is done so as to allow respect for the radial evolution of the Mach triangle at the entrance of the moving wheel.
  • the changing profile of the blades 103 is such that the blades are free of angular parts with the exception of the leading edges and trailing edges which can advantageously be truncated.
  • the vanes 103 can be manufactured separately and attached to the hub 101.
  • the vanes 103 can be anchored in the hub 101 and the outer casing 102 by shaped ends 138, 139 of fir foot.
  • a vane distributor according to the invention can advantageously be produced according to the technology of powder metallurgy.
  • the vanes 103 may have various inclinations at the outlet depending on the applications envisaged.
  • the inclination of the blades 103 relative to the axis of the distributor can be between approximately 65 and 80 °.
  • Figure 7 relates to the previous example and shows the triangles of the speeds upstream of the turbine rotor at the foot (vectors A, A '), an average radius (vectors B, B') and the head ( vectors C, C ').
  • the vectors A, B, C give the output speed values in Mach number (namely respectively 1.86; 1.74 and 1.63) for an absolute inclination ⁇ a of 74 °, for the foot, at the mean radius and the head of the blades 103.
  • the vectors A ', B', C ' give the values of speed relative to the input of the rotor in Mach number (namely 1.55; 1.42 and 1.31 respectively) for a relative angle ⁇ r which is 70.7 ° respectively; 70.3 ° and 69.9 ° at the level of the foot, the middle radius and the head of the vanes 103 of the distributor.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
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 true EP0719906A1 (de) 1996-07-03
EP0719906B1 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)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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

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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
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
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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GB191421322A (en) * 1913-10-31 1914-12-10 Escher Wyss Maschf Ag Improvements in Steam and Gas Turbines.
US1801427A (en) * 1927-03-12 1931-04-21 Holzwarth Gas Turbine Co Gas-turbine blade
DE1426789B1 (de) * 1965-04-01 1970-04-16 Bbc Brown Boveri & Cie Laufschaufel fuer thermische,axial durchstroemte Stroemungsmaschinen
DE2002348A1 (de) * 1969-01-24 1970-07-30 Gen Electric Turbinenschaufeln von Axialstromturbinen
GB1420318A (en) * 1972-11-04 1976-01-07 Rolls Royce Method and apparatus for manufaccturing an article from a particulate material
FR2560287A1 (fr) 1984-02-27 1985-08-30 Rockwell International Corp Tuyere de stator et moteur a turbine

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Publication number Priority date Publication date Assignee Title
GB191421322A (en) * 1913-10-31 1914-12-10 Escher Wyss Maschf Ag Improvements in Steam and Gas Turbines.
US1801427A (en) * 1927-03-12 1931-04-21 Holzwarth Gas Turbine Co Gas-turbine blade
DE1426789B1 (de) * 1965-04-01 1970-04-16 Bbc Brown Boveri & Cie Laufschaufel fuer thermische,axial durchstroemte Stroemungsmaschinen
DE2002348A1 (de) * 1969-01-24 1970-07-30 Gen Electric Turbinenschaufeln von Axialstromturbinen
GB1420318A (en) * 1972-11-04 1976-01-07 Rolls Royce Method and apparatus for manufaccturing an article from a particulate material
FR2560287A1 (fr) 1984-02-27 1985-08-30 Rockwell International Corp Tuyere de stator et moteur a turbine

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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

Also Published As

Publication number Publication date
JP3779360B2 (ja) 2006-05-24
FR2728618B1 (fr) 1997-03-14
EP0719906B1 (de) 1999-04-14
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
JPH08232603A (ja) 1996-09-10

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