EP0355312B1 - Axialdurchströmte Turbine mit radial-axialer erster Stufe - Google Patents
Axialdurchströmte Turbine mit radial-axialer erster Stufe Download PDFInfo
- Publication number
- EP0355312B1 EP0355312B1 EP89111439A EP89111439A EP0355312B1 EP 0355312 B1 EP0355312 B1 EP 0355312B1 EP 89111439 A EP89111439 A EP 89111439A EP 89111439 A EP89111439 A EP 89111439A EP 0355312 B1 EP0355312 B1 EP 0355312B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- radial
- axial
- turbine
- inflow
- 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.)
- Expired - Lifetime
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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 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 Inflow housing is acted upon, and the radial guide vanes are provided at their two ends with base plates with which they are vane-shaped in the vane carrier in annular recesses.
- 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 average inflow speed to be increased by a multiple of the values customary for toroidal inlet ducts, without achieving 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 usual separate force-absorbing auxiliary constructions in a turbine of the type mentioned at the outset.
- this object is achieved in that the free ends of the foot plates are spherical.
- 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 cooperation 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 vane carriers 5, which are equipped with the guide vanes 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.
- 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 base plate at each end.
- 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 inner and outer sides 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 airfoil 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 sketched. 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)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CH2938/88 | 1988-08-03 | ||
CH2938/88A CH676735A5 (US08124317-20120228-C00038.png) | 1988-08-03 | 1988-08-03 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0355312A1 EP0355312A1 (de) | 1990-02-28 |
EP0355312B1 true EP0355312B1 (de) | 1993-02-10 |
Family
ID=4245010
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP89111439A Expired - Lifetime EP0355312B1 (de) | 1988-08-03 | 1989-06-23 | Axialdurchströmte Turbine mit radial-axialer erster Stufe |
Country Status (5)
Families Citing this family (23)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6609881B2 (en) * | 2001-11-15 | 2003-08-26 | General Electric Company | Steam turbine inlet and methods of retrofitting |
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 |
DE102010027808A1 (de) * | 2010-04-15 | 2011-10-20 | Siemens Aktiengesellschaft | Drallerzeuger für einen Brenner |
DE102011119879A1 (de) * | 2011-12-01 | 2013-06-06 | Ihi Charging Systems International Gmbh | Fluidenergiemaschine, insbesondere für einen Abgasturbolader eines Kraftwagens |
CN105324554B (zh) * | 2013-06-28 | 2017-05-24 | 三菱重工压缩机有限公司 | 轴流膨胀机 |
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 |
EP2851515A1 (de) * | 2013-09-24 | 2015-03-25 | Siemens Aktiengesellschaft | Anordnung zur Befestigung von Turbinenschaufeln |
US9739238B2 (en) | 2015-03-09 | 2017-08-22 | Caterpillar Inc. | Turbocharger and method |
US9650913B2 (en) | 2015-03-09 | 2017-05-16 | Caterpillar Inc. | Turbocharger turbine containment structure |
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 |
US9903225B2 (en) | 2015-03-09 | 2018-02-27 | Caterpillar Inc. | Turbocharger with low carbon steel shaft |
US9915172B2 (en) | 2015-03-09 | 2018-03-13 | Caterpillar Inc. | Turbocharger with bearing piloted compressor wheel |
US9752536B2 (en) | 2015-03-09 | 2017-09-05 | Caterpillar Inc. | Turbocharger and method |
US9683520B2 (en) | 2015-03-09 | 2017-06-20 | Caterpillar Inc. | Turbocharger and method |
US9822700B2 (en) | 2015-03-09 | 2017-11-21 | Caterpillar Inc. | Turbocharger with oil containment arrangement |
US9890788B2 (en) | 2015-03-09 | 2018-02-13 | Caterpillar Inc. | Turbocharger and method |
US9879594B2 (en) | 2015-03-09 | 2018-01-30 | Caterpillar Inc. | Turbocharger turbine nozzle and containment structure |
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 (en) | 2020-09-10 | 2024-04-03 | General Electric Technology GmbH | Nozzle segment, steam turbine with diaphragm of multiple nozzle segments and method for assembly thereof |
Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
USB563412I5 (US08124317-20120228-C00038.png) * | 1975-03-28 | 1976-02-24 |
Family Cites Families (18)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US563412A (en) * | 1896-07-07 | Automatic lighting device | ||
DE526805C (de) * | 1931-06-10 | Fried Krupp Germaniawerft Akt | Leitschaufel-Anordnung fuer axial beaufschlagte Doppelstrom-Dampfturbinen | |
US1935463A (en) * | 1931-03-13 | 1933-11-14 | Wiberg Oscar Anton | Casing for steam or gas turbines |
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 |
DE1751947B2 (de) * | 1968-08-22 | 1978-05-11 | Aeg-Kanis Turbinenfabrik Gmbh, 8500 Nuernberg | Dampf- oder Gasturbine mit Mengenregelung |
CH545414A (de) * | 1972-05-31 | 1973-12-15 | Bbc Brown Boveri & Cie | Erste Stufe einer zweiflutigen Niederdruck-Dampfturbine grosser Leistung |
CH564680A5 (US08124317-20120228-C00038.png) * | 1973-10-16 | 1975-07-31 | Bbc Brown Boveri & Cie | |
US3910716A (en) * | 1974-05-23 | 1975-10-07 | Westinghouse Electric Corp | Gas turbine inlet vane structure utilizing a stable ceramic spherical interface arrangement |
CS174516B1 (US08124317-20120228-C00038.png) * | 1974-09-26 | 1977-04-29 | ||
CH579212A5 (US08124317-20120228-C00038.png) * | 1974-12-16 | 1976-08-31 | Bbc Brown Boveri & Cie | |
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 |
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 |
-
1988
- 1988-08-03 CH CH2938/88A patent/CH676735A5/de not_active IP Right Cessation
-
1989
- 1989-06-23 EP EP89111439A patent/EP0355312B1/de not_active Expired - Lifetime
- 1989-06-23 DE DE8989111439T patent/DE58903508D1/de not_active Expired - Lifetime
- 1989-06-28 US US07/372,456 patent/US4948333A/en not_active Expired - Lifetime
- 1989-08-02 JP JP1199534A patent/JP2996674B2/ja not_active Expired - Fee Related
Patent Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
USB563412I5 (US08124317-20120228-C00038.png) * | 1975-03-28 | 1976-02-24 |
Also Published As
Publication number | Publication date |
---|---|
JP2996674B2 (ja) | 2000-01-11 |
CH676735A5 (US08124317-20120228-C00038.png) | 1991-02-28 |
EP0355312A1 (de) | 1990-02-28 |
JPH0270905A (ja) | 1990-03-09 |
US4948333A (en) | 1990-08-14 |
DE58903508D1 (de) | 1993-03-25 |
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