EP0355312A1 - Turbine axiale avec premier étage radial-axial - Google Patents

Turbine axiale avec premier étage radial-axial Download PDF

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Publication number
EP0355312A1
EP0355312A1 EP89111439A EP89111439A EP0355312A1 EP 0355312 A1 EP0355312 A1 EP 0355312A1 EP 89111439 A EP89111439 A EP 89111439A EP 89111439 A EP89111439 A EP 89111439A EP 0355312 A1 EP0355312 A1 EP 0355312A1
Authority
EP
European Patent Office
Prior art keywords
radial
turbine
axial
base plates
stage
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
EP89111439A
Other languages
German (de)
English (en)
Other versions
EP0355312B1 (fr
Inventor
Hans-Peter Meer
Ueli Wieland
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.)
ABB Asea Brown Boveri Ltd
ABB AB
Original Assignee
ABB Asea Brown Boveri Ltd
Asea Brown Boveri AB
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 ABB Asea Brown Boveri Ltd, Asea Brown Boveri AB filed Critical ABB Asea Brown Boveri Ltd
Publication of EP0355312A1 publication Critical patent/EP0355312A1/fr
Application granted granted Critical
Publication of EP0355312B1 publication Critical patent/EP0355312B1/fr
Anticipated expiration legal-status Critical
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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
    • F01D9/048—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector for radial admission

Definitions

  • the invention relates to an axially flow-through turbine, consisting essentially of an outer housing, an inner housing with preferably integrated guide vane carrier and a rotor equipped with rotor blades, in which turbine the first stage is designed as a radial-axial stage, the radial guide row consisting of a toroidal or a spiral-shaped inflow housing is acted upon.
  • the inflow to axial blading, in particular of low-pressure parts of steam turbines, can take place via a toroidal annular space.
  • This has the task of feeding the amount of steam entering this annular space through one or more pipe sections as evenly as possible and avoiding major losses to the first blade ring. Due to the limited number and the often asymmetrical arrangement of the supply pipe sockets, this cannot be achieved sufficiently.
  • the large number of necessary deflections of the flow until the radial blade channel is reached leads to losses which can reach a multiple of the kinetic inflow energy in the pipe socket. For this reason, efforts are being made to keep the average speeds in the annulus as low as possible, which leads to large dimensions of the annulus leads.
  • a radial guide vane is therefore arranged in the radial inflow part, which generates the swirl required to generate power in the first impeller.
  • a turbine is known, for example from DE-A-2 358 160.
  • a spiral design of the inflow housing allows the mean inflow speed to be increased by a multiple of the values customary for toroidal inlet ducts without reaching their great losses. This is made possible by the fact that the flow direction, which takes place in the inlet connection and in the spiral predominantly in the tangential direction in the same direction as the turbine rotation direction, can be used directly for generating work. In contrast, the increased friction losses due to the higher speeds are less significant.
  • By suitably designing the cross sections of the spiral a uniform inflow to the radial blade channel can be achieved and a radial guide vane arranged there will only deflect the flow weakly and thus with little loss.
  • Such a turbine is known for example from DE-A-2 503 493.
  • the inflow housings are usually provided with reinforcing ribs to absorb force as a result of different expansions during operation, or else bars are provided in the radial channel upstream of the radial guide row, as can be seen in the aforementioned DE-A-2 358 160 . It goes without saying that such internals do not represent insignificant flow resistances.
  • the invention seeks to remedy this. It is based on the task of dispensing with the separate force-absorbing auxiliary structures such as reinforcing ribs or reinforcing bolts in a turbine of the type mentioned at the outset.
  • this object is achieved in that the radial blades are provided at their two ends with base plates with which they are shoveled in ring-shaped recesses in the blade carrier and in that the free ends of the base plates are spherical.
  • the radial guide vanes also perform a static function in addition to their deflecting function, leads to the advantage that - On the one hand, a gain in space can be achieved in the radial direction in that the radially flowing part of the guide vane carrier can be made shorter in its extent, and - on the other hand, that in the case of housings with a 360 ° inflow spiral, there is no possibility of the usual bolts is created to design completely one-piece inner housing.
  • the arcuate circumferential surfaces of the base plates of the radial guide vanes are dimensioned in such a way that they have a play in relation to the annular recesses of the blade carrier.
  • the foot plates should then be rotated relative to one another for the purpose of defining these arcuate peripheral surfaces in the indentations. In conjunction with the spherical end faces of the base plates, this measure creates a locally defined line of force that always runs within the blade profile.
  • both base plates are provided on their arcuate circumferential surfaces with ring grooves, in which spikes of the twists engage.
  • tensile forces can also be introduced into the guide vane carrier via the guide vanes.
  • the main components are the outer housing 1, the inner housing 2 and the rotor 3.
  • the outer housing consists of several parts, not specified, which are usually screwed or welded together only at the place of installation.
  • the cast inner housing consists of the inflow housing 4 in the form of a 360 ° spiral and the downstream guide blade carriers 5, which are equipped with the guide blades 6.
  • the guide vane carriers are connected to the spiral housing by screwing.
  • the invention also provides the possibility of producing the inner housing in one piece.
  • One-part is to be understood here relatively, because the spiral housing and blade carrier are of course horizontally divided and screwed together on the separating flanges, not shown. In the plane This separating flange supports the inner housing in the outer housing by means of support arms.
  • the rotor 3 equipped with the rotor blades 7 is welded together from shaft washers and shaft ends with integrated coupling flanges. It is supported in the bearing housings 8 by means of slide bearings.
  • the path of the steam leads from an additional steam line 9 via the steam feedthrough in the outer housing 1 into the inner housing 2.
  • the spiral ensures that the steam reaches the two flows of the blading in a well-guided manner.
  • Optimal efficiency is achieved with the radially arranged first guide row 10.
  • FIG. 2 shows how the radial guide vanes 10 are suspended in the radial part of the inflow channel 4 in a double-flow turbine.
  • the airfoil is provided with a footplate at both ends.
  • the left footplate 14a is in the axial direction of the turbomachine, i.e. dimensioned shorter in the longitudinal direction of the radial blade than the right foot plate 14b.
  • Both footplates are in annular recesses 15a, respectively. 15b a.
  • the right foot plates 14b are provided with a groove 16 into which an annular prong 17 protruding in the recess 15b engages.
  • the peripheral surfaces 18a and. 18b on the inside and outside of the rhombus-shaped base plates are milled in an arc (FIGS. 4a, 5a), the respective radius of the arc corresponding to the radius of the associated indentation.
  • the free end faces 19 of the two base plates are designed to be spherical for bearing against the radial parts of the indentations.
  • the curvature is chosen so that the contact points are always on a line that lies within the blade profile.
  • a defined play 20 is provided between the arcuate peripheral surfaces 18 and the corresponding walls of the recess 15.
  • the radial parts of the indentations can roll over the spherical end faces of the base plates.
  • the pressure loads that occur are absorbed by the blade without it buckling. This is particularly important in the case of a 360 ° spiral according to FIG. 1, since such spirals stretch differently over the circumference.
  • the radial guide row could be overstressed, since in addition to the pressure load, the bending stress would also have to be absorbed.
  • the two base plates 14a and 14b are rotated relative to one another by a certain angular dimension, for example 0.5 °. When shoveling in, this leads to a clear contact of the circumferential surfaces in the recesses, as is clearly shown in FIGS. 4a and 5a.
  • Fig. 3 shows a variant of the guide vane attachment, which is suitable for absorbing both tensile and compressive forces.
  • the same base plates 14c are provided, which are shoveled in the manner of the hammer head known per se.
  • the arcuate peripheral surfaces 18c of both the inner and the outer plate sides are provided with grooves 16, in which correspondingly sized prongs 17 of the recess 15c engage.
  • FIG. 4 the arrangement of the radial guide row in an annular or. toroidal installation sketchy posed. Due to the prevailing flow conditions, according to FIG. 4a, a vane profile has been selected for the guide vanes, which is relatively insensitive to the inflow direction, which varies greatly over the circumference.
  • FIG. 5 finally shows the inflow conditions in an inflow housing which consists of two 180 ° spirals. It can be seen here that, according to FIG. 5a, a grating with only weak deflection and therefore extremely low losses can be used.
  • the invention is not limited to the examples shown and described.
  • the invention can also be successfully used in the inflow housings of single-flow turbines, provided that they are provided with a radial first guide row.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP89111439A 1988-08-03 1989-06-23 Turbine axiale avec premier étage radial-axial Expired - Lifetime EP0355312B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH2938/88 1988-08-03
CH2938/88A CH676735A5 (fr) 1988-08-03 1988-08-03

Publications (2)

Publication Number Publication Date
EP0355312A1 true EP0355312A1 (fr) 1990-02-28
EP0355312B1 EP0355312B1 (fr) 1993-02-10

Family

ID=4245010

Family Applications (1)

Application Number Title Priority Date Filing Date
EP89111439A Expired - Lifetime EP0355312B1 (fr) 1988-08-03 1989-06-23 Turbine axiale avec premier étage radial-axial

Country Status (5)

Country Link
US (1) US4948333A (fr)
EP (1) EP0355312B1 (fr)
JP (1) JP2996674B2 (fr)
CH (1) CH676735A5 (fr)
DE (1) DE58903508D1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1312759A3 (fr) * 2001-11-15 2009-07-29 General Electric Company Manchon d'admission d'une turbine à vapeur et procédé d'installation rétroactive de ce dernier
WO2011128179A1 (fr) * 2010-04-15 2011-10-20 Siemens Aktiengesellschaft Générateur de turbulence pour un brûleur

Families Citing this family (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7762766B2 (en) * 2006-07-06 2010-07-27 Siemens Energy, Inc. Cantilevered framework support for turbine vane
US8240045B2 (en) * 2007-05-22 2012-08-14 Siemens Energy, Inc. Gas turbine transition duct coupling apparatus
DE102008062078B4 (de) * 2008-12-16 2019-10-17 Man Energy Solutions Se Eintrittsstufe für eine Dampfturbine
US8616007B2 (en) * 2009-01-22 2013-12-31 Siemens Energy, Inc. Structural attachment system for transition duct outlet
DE102011119879A1 (de) * 2011-12-01 2013-06-06 Ihi Charging Systems International Gmbh Fluidenergiemaschine, insbesondere für einen Abgasturbolader eines Kraftwagens
JP6483106B2 (ja) 2013-06-28 2019-03-13 エクソンモービル アップストリーム リサーチ カンパニー 軸流膨張機を利用するシステム及び方法
EP3014077B1 (fr) * 2013-06-28 2018-01-17 Mitsubishi Heavy Industries Compressor Corporation Détendeur à flux axial
EP2851515A1 (fr) * 2013-09-24 2015-03-25 Siemens Aktiengesellschaft Agencement de fixation d'aubes de turbine
US9739238B2 (en) 2015-03-09 2017-08-22 Caterpillar Inc. Turbocharger and method
US9879594B2 (en) 2015-03-09 2018-01-30 Caterpillar Inc. Turbocharger turbine nozzle and containment structure
US9752536B2 (en) 2015-03-09 2017-09-05 Caterpillar Inc. Turbocharger and method
US9650913B2 (en) 2015-03-09 2017-05-16 Caterpillar Inc. Turbocharger turbine containment structure
US9903225B2 (en) 2015-03-09 2018-02-27 Caterpillar Inc. Turbocharger with low carbon steel shaft
US9890788B2 (en) 2015-03-09 2018-02-13 Caterpillar Inc. Turbocharger and method
US9683520B2 (en) 2015-03-09 2017-06-20 Caterpillar Inc. Turbocharger and method
US9915172B2 (en) 2015-03-09 2018-03-13 Caterpillar Inc. Turbocharger with bearing piloted compressor wheel
US9732633B2 (en) 2015-03-09 2017-08-15 Caterpillar Inc. Turbocharger turbine assembly
US9638138B2 (en) 2015-03-09 2017-05-02 Caterpillar Inc. Turbocharger and method
US9822700B2 (en) 2015-03-09 2017-11-21 Caterpillar Inc. Turbocharger with oil containment arrangement
CN106050322A (zh) * 2016-08-08 2016-10-26 中国船舶重工集团公司第七�三研究所 一种倾斜轴式变几何动力涡轮导叶
EP3967846B1 (fr) 2020-09-10 2024-04-03 General Electric Technology GmbH Segment de vane, turbine à vapeur dotée d'un diaphragme de multiples segments de vane et procédé d'assemblage correspondant

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1935463A (en) * 1931-03-13 1933-11-14 Wiberg Oscar Anton Casing for steam or gas turbines
FR2016189A1 (fr) * 1968-08-22 1970-05-08 Aeg Kanis Turbinen
CH545414A (de) * 1972-05-31 1973-12-15 Bbc Brown Boveri & Cie Erste Stufe einer zweiflutigen Niederdruck-Dampfturbine grosser Leistung
US3910716A (en) * 1974-05-23 1975-10-07 Westinghouse Electric Corp Gas turbine inlet vane structure utilizing a stable ceramic spherical interface arrangement
USB563412I5 (fr) * 1975-03-28 1976-02-24
US4053257A (en) * 1976-02-20 1977-10-11 Westinghouse Electric Corporation Stator vane assembly for gas turbines
US4076451A (en) * 1976-03-05 1978-02-28 United Technologies Corporation Ceramic turbine stator

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US563412A (en) * 1896-07-07 Automatic lighting device
DE526805C (de) * 1931-06-10 Fried Krupp Germaniawerft Akt Leitschaufel-Anordnung fuer axial beaufschlagte Doppelstrom-Dampfturbinen
US2281631A (en) * 1939-10-06 1942-05-05 Worthington Pump & Mach Corp Centrifugal pump
US3305165A (en) * 1963-12-20 1967-02-21 Alfred T Gregory Elastic fluid compressor
US3263963A (en) * 1964-11-05 1966-08-02 Worthington Corp Nozzle blade assembly comprising replaceable and adjustable nozzle blades
US3313517A (en) * 1965-04-01 1967-04-11 Worthington Corp Gas expander turbines for power recovery use with jet type, hot gas generators
CH564680A5 (fr) * 1973-10-16 1975-07-31 Bbc Brown Boveri & Cie
CS174516B1 (fr) * 1974-09-26 1977-04-29
CH579212A5 (fr) * 1974-12-16 1976-08-31 Bbc Brown Boveri & Cie
JPS5919407B2 (ja) * 1979-06-18 1984-05-07 松下電子工業株式会社 陰極線管用電子銃
JPS564722A (en) * 1979-06-25 1981-01-19 Murata Machinery Ltd Production of crimp yarn
JPS62271903A (ja) * 1986-05-21 1987-11-26 Mitsubishi Heavy Ind Ltd タ−ビン翼

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1935463A (en) * 1931-03-13 1933-11-14 Wiberg Oscar Anton Casing for steam or gas turbines
FR2016189A1 (fr) * 1968-08-22 1970-05-08 Aeg Kanis Turbinen
CH545414A (de) * 1972-05-31 1973-12-15 Bbc Brown Boveri & Cie Erste Stufe einer zweiflutigen Niederdruck-Dampfturbine grosser Leistung
US3910716A (en) * 1974-05-23 1975-10-07 Westinghouse Electric Corp Gas turbine inlet vane structure utilizing a stable ceramic spherical interface arrangement
USB563412I5 (fr) * 1975-03-28 1976-02-24
US4053257A (en) * 1976-02-20 1977-10-11 Westinghouse Electric Corporation Stator vane assembly for gas turbines
US4076451A (en) * 1976-03-05 1978-02-28 United Technologies Corporation Ceramic turbine stator

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1312759A3 (fr) * 2001-11-15 2009-07-29 General Electric Company Manchon d'admission d'une turbine à vapeur et procédé d'installation rétroactive de ce dernier
WO2011128179A1 (fr) * 2010-04-15 2011-10-20 Siemens Aktiengesellschaft Générateur de turbulence pour un brûleur

Also Published As

Publication number Publication date
CH676735A5 (fr) 1991-02-28
JP2996674B2 (ja) 2000-01-11
JPH0270905A (ja) 1990-03-09
EP0355312B1 (fr) 1993-02-10
US4948333A (en) 1990-08-14
DE58903508D1 (de) 1993-03-25

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