WO2005019604A1 - Dispositif de guidage de flux dans le diffuseur d'une turbomachine, et procede pour devier un flux - Google Patents
Dispositif de guidage de flux dans le diffuseur d'une turbomachine, et procede pour devier un flux Download PDFInfo
- Publication number
- WO2005019604A1 WO2005019604A1 PCT/EP2004/007252 EP2004007252W WO2005019604A1 WO 2005019604 A1 WO2005019604 A1 WO 2005019604A1 EP 2004007252 W EP2004007252 W EP 2004007252W WO 2005019604 A1 WO2005019604 A1 WO 2005019604A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- outflow
- guide
- deflection surface
- rotor
- guide device
- Prior art date
Links
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
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
- F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
- F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
-
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
- F01D25/162—Bearing supports
-
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/30—Exhaust heads, chambers, or the like
-
- 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
- F05D2250/00—Geometry
- F05D2250/40—Movement of components
- F05D2250/41—Movement of components with one degree of freedom
- F05D2250/411—Movement of components with one degree of freedom in rotation
-
- 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
- F05D2260/00—Function
- F05D2260/70—Adjusting of angle of incidence or attack of rotating blades
- F05D2260/74—Adjusting of angle of incidence or attack of rotating blades by turning around an axis perpendicular the rotor centre line
Definitions
- the invention relates to an outflow guide device in a diffuser of a turbomachine with a guide blade, which has a leading edge and a trailing edge, between which a deflection surface is provided and which deflects a flow medium from an incident direction, and a method for changing an outflow guide device.
- a gas turbine as an example of a turbomachine
- intake air is compressed and heated in the compressor part and then strongly heated and accelerated in a combustion chamber with the addition of a fuel.
- a multi-stage turbine connects to the combustion chamber in terms of flow.
- the flow medium which is a mixture of the burned fuel and the compressed air, flows through the multi-stage turbine.
- the movement of the flow medium creates an angular momentum on the rotor and thus ultimately leads to a rotation of the rotor.
- the rotational energy is then converted into electrical energy using a generator.
- the flow medium flows in a diffuser past a bearing star, which has several guide blades.
- the bearing star serves on the one hand for deflecting the flow medium and on the other hand as a holder for the rotatably mounted rotor.
- the bearing star and in particular the guide blades are usually made rigid and of the same material.
- Such a bearing star arrangement is described in document DE 39 42 203.
- the bearing star arrangement there relates to a turbine engine.
- the object of the present invention is to provide an outflow guiding device with which flow losses in a diffuser can be reduced.
- Another object is to provide a method for changing an outflow guide device in a diffuser to reduce the flow losses.
- the object directed to the outflow guiding device is achieved by an outflow guiding device
- Turbomachine with a guide blade which has a leading edge and a trailing edge between which a deflecting surface is provided which deflects a flow medium from an incident direction
- the outflow guiding device being mountable in a diffuser
- the outflow guiding device comprising a rotor-side end and a stator-side end and the rotor-side End is designed to support a rotor
- the guide blade being adjustable with respect to the course of its deflection surface relative to the direction of incidence.
- the object directed towards the method is achieved by a method for changing an outflow guide device of a turbomachine with a guide blade, which has a leading edge and a trailing edge between which a deflection surface is provided which deflects a flow medium from an incident direction, the outflow guide device in a diffuser is installed, a rotor-side end and a stator-side end being provided for the outflow guiding device and the rotor-side end supporting the rotor, a course of the deflection surface of the guide blade being adjustable relative to the incident sighting.
- the advantage can be seen, inter alia, in the fact that a flow of a flow medium through the outflow guiding device can be changed in a targeted manner, and thereby an inflow of the Lagersterns is improved.
- Another advantage is that the outflow guiding device can be adjusted during the intended operation.
- Another advantage is that an exhaust gas swirl is reduced and, furthermore, the flow is improved for each load state of the turbine or operating state of the turbine.
- the guide blade is preferably designed in such a way that the deflection surface can be rotated.
- the guide sheet is rotatably mounted about an axis of rotation.
- the axis of rotation is essentially perpendicular to the direction of incidence. This changes the overall aerodynamics of the blade.
- the outer shape of the deflection surface is preferably designed to be adjustable.
- the guide sheet comprises a front part located in the leading edge and a rear part located in the trailing edge.
- the rear part located in the trailing edge is rotatably supported about an axis of rotation.
- the axis of rotation is essentially parallel to the trailing edge.
- the front part which is usually very solid, can be rigidly installed in the diffuser.
- the rear part which is rotatably supported, improves the inflow through the outflow guide device due to the changeable aerodynamics.
- the rear part is preferably designed in such a way that the rear part is moved in a flow direction that runs directly from the leading edge to the trailing edge.
- the length in the flow direction of a respective guide sheet can hereby be changed individually.
- the guide sheet can be shortened or lengthened in the direction of flow.
- Figure 1 is a perspective view of a prior art power stage of a gas turbine
- FIG. 2 shows a perspective illustration of a guide sheet of an outflow guide device belonging to the prior art
- Figure 3 is a cross-sectional view of a guide sheet in a first embodiment
- Figure 4 is a cross-sectional view of a guide sheet in a second embodiment
- Figure 5 is a cross-sectional view of a guide sheet in a third embodiment.
- FIG. 1 shows a perspective illustration of a gas turbine 1 belonging to the prior art.
- An end turbine stage 3 which comprises a plurality of moving blades 4, is attached to a rotatably mounted rotor 2.
- An outer housing is arranged around the rotor 2 and has a lower part 5a and an upper part 5b.
- the rotor 2 is rotatably mounted about an axis of rotation 6.
- a flow medium flows parallel to the axis of rotation 6 in the direction of the turbine stage 3.
- the flow medium flows into the diffuser 7.
- the flow medium flows through an incident direction through a so-called bearing star, which is also referred to as a discharge guide device 8.
- the outflow guide device 8 comprises six guide blades 9. In alternative embodiments, fewer or more than six guide blades 9 are possible.
- the flow medium flows out at a varying outflow angle after turbine stage 3.
- the outflow angle depends on a load attached to the rotor 2.
- the outflow guiding device 8 comprises a rotor-side end 10 and a stator-side end 11.
- the rotor-side end 10 is designed such that the rotor 2 is rotatably mounted therein.
- Figure 2 is a perspective view of a
- a flow medium flows to the guide blade 9 in an incident direction 12.
- the incident direction 12 depends on the outflow angle.
- the flow medium is true 'first to a leading edge 13, flows around a respective environmental guide surface 15 and then flows from a trailing edge 14 from the gas turbine 1 out.
- the guide sheet 9 is designed such that the guide sheet 9 can be adjusted with respect to the course of its deflecting surface 15 relative to the direction of incidence 12.
- This configuration of the guide blade 9 minimizes losses which are caused by non-optimal flow against the guide blade 9 as a result of the load-dependent varying outflow angle.
- the deflection surface (15) can be rotatable.
- the outer shape of the deflection surface (15) can be adjustable.
- a first embodiment is shown in FIG. 3.
- a cross section of the guide leaf 9 can be seen in FIG. The viewing direction is essentially perpendicular to the direction of incidence 12 in the direction of the axis of rotation 6.
- the guide blade 9 is in this case rotatably mounted about an axis of rotation 16.
- This axis of rotation 16 is essentially perpendicular to the direction of incidence 12.
- the axis of rotation 16 lies essentially in the center of the guide blade 9.
- the axis of rotation 6 can also be attached closer to the leading edge 13 or the trailing edge 14.
- the guide sheet 9 is rotated about the axis of rotation 16.
- the guide sheet 9 is rotated about the axis of rotation 16 either clockwise 17 or counterclockwise 18.
- a flow medium that impinges on the guide blade 9 in the direction of incidence 12 can thereby be deflected.
- the guide sheet 9 comprises a front part 20 comprising the leading edge 13 and a rear part 19 comprising the trailing edge 14.
- the front part 20 is of rigid construction.
- the front part 20 can also be rotatably supported about a further axis of rotation.
- the rear part 19 is designed such that it is rotatably mounted about an axis of rotation 21.
- the axis of rotation 21 is attached in a front region 22 of the rear part 19.
- a rear region 23 can thereby be moved either clockwise 17 or counterclockwise 18.
- a third embodiment of the guide sheet 9 can be seen in FIG.
- the rear part 19 is moved in the flow direction either to the direction of incidence (represented by arrow 24) or counter to the direction of incidence (represented by arrow 25).
- the front part 20 of the guide sheet 9 can be rotatably mounted about an additional axis of rotation in an alternative embodiment.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Control Of Turbines (AREA)
Abstract
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP04740600A EP1651842A1 (fr) | 2003-08-08 | 2004-07-02 | Dispositif de guidage dans un passage d'echappement pour une turbomachine et procede d'operation |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP03018164.8 | 2003-08-08 | ||
EP03018164A EP1505263A1 (fr) | 2003-08-08 | 2003-08-08 | Dispositif de guidage dans un passage d'échappement pour une turbomachine et procédé d'opération |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2005019604A1 true WO2005019604A1 (fr) | 2005-03-03 |
Family
ID=33547671
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/EP2004/007252 WO2005019604A1 (fr) | 2003-08-08 | 2004-07-02 | Dispositif de guidage de flux dans le diffuseur d'une turbomachine, et procede pour devier un flux |
Country Status (2)
Country | Link |
---|---|
EP (2) | EP1505263A1 (fr) |
WO (1) | WO2005019604A1 (fr) |
Families Citing this family (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US7632064B2 (en) | 2006-09-01 | 2009-12-15 | United Technologies Corporation | Variable geometry guide vane for a gas turbine engine |
US9032721B2 (en) * | 2011-12-14 | 2015-05-19 | Siemens Energy, Inc. | Gas turbine engine exhaust diffuser including circumferential vane |
EP2644838A1 (fr) * | 2012-03-27 | 2013-10-02 | Alstom Technology Ltd | Boîtier de gaz d'échappement d'une turbine à gaz |
US9422864B2 (en) | 2012-12-20 | 2016-08-23 | General Electric Company | Staggered double row, slotted airfoil design for gas turbine exhaust frame |
DE102020209792A1 (de) | 2020-08-04 | 2022-02-10 | MTU Aero Engines AG | Leitschaufel |
Citations (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CH247831A (de) * | 1942-11-26 | 1947-03-31 | Jendrassik Georg | Turbine für heisses Arbeitsmittel. |
US2934895A (en) * | 1958-09-15 | 1960-05-03 | Curtiss Wright Corp | Dual cycle engine distributor construction |
US2945672A (en) * | 1956-10-05 | 1960-07-19 | Marquardt Corp | Gas turbine unit |
US3285567A (en) * | 1963-11-29 | 1966-11-15 | Bristol Siddeley Engines Ltd | Axial flow turbines and compressors |
US3563669A (en) * | 1969-07-10 | 1971-02-16 | Gen Motors Corp | Variable area nozzle |
US4292802A (en) * | 1978-12-27 | 1981-10-06 | General Electric Company | Method and apparatus for increasing compressor inlet pressure |
FR2526485A1 (fr) * | 1982-05-07 | 1983-11-10 | Snecma | Roue directrice d'entree de soufflante de turboreacteur permettant le demontage unitaire des aubes mobiles, et procede pour la mise en oeuvre |
EP0094296A1 (fr) * | 1982-05-04 | 1983-11-16 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." | Dispositif de réglage de la perte de charge d'au moins un des flux dans un turboréacteur multiflux |
US4972671A (en) * | 1988-05-11 | 1990-11-27 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." | Turbo-engine air intake grill |
US4989406A (en) * | 1988-12-29 | 1991-02-05 | General Electric Company | Turbine engine assembly with aft mounted outlet guide vanes |
US5259187A (en) * | 1993-02-05 | 1993-11-09 | General Electric Company | Method of operating an aircraft bypass turbofan engine having variable fan outlet guide vanes |
-
2003
- 2003-08-08 EP EP03018164A patent/EP1505263A1/fr not_active Withdrawn
-
2004
- 2004-07-02 EP EP04740600A patent/EP1651842A1/fr not_active Withdrawn
- 2004-07-02 WO PCT/EP2004/007252 patent/WO2005019604A1/fr not_active Application Discontinuation
Patent Citations (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CH247831A (de) * | 1942-11-26 | 1947-03-31 | Jendrassik Georg | Turbine für heisses Arbeitsmittel. |
US2945672A (en) * | 1956-10-05 | 1960-07-19 | Marquardt Corp | Gas turbine unit |
US2934895A (en) * | 1958-09-15 | 1960-05-03 | Curtiss Wright Corp | Dual cycle engine distributor construction |
US3285567A (en) * | 1963-11-29 | 1966-11-15 | Bristol Siddeley Engines Ltd | Axial flow turbines and compressors |
US3563669A (en) * | 1969-07-10 | 1971-02-16 | Gen Motors Corp | Variable area nozzle |
US4292802A (en) * | 1978-12-27 | 1981-10-06 | General Electric Company | Method and apparatus for increasing compressor inlet pressure |
EP0094296A1 (fr) * | 1982-05-04 | 1983-11-16 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." | Dispositif de réglage de la perte de charge d'au moins un des flux dans un turboréacteur multiflux |
FR2526485A1 (fr) * | 1982-05-07 | 1983-11-10 | Snecma | Roue directrice d'entree de soufflante de turboreacteur permettant le demontage unitaire des aubes mobiles, et procede pour la mise en oeuvre |
US4972671A (en) * | 1988-05-11 | 1990-11-27 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." | Turbo-engine air intake grill |
US4989406A (en) * | 1988-12-29 | 1991-02-05 | General Electric Company | Turbine engine assembly with aft mounted outlet guide vanes |
US5259187A (en) * | 1993-02-05 | 1993-11-09 | General Electric Company | Method of operating an aircraft bypass turbofan engine having variable fan outlet guide vanes |
Also Published As
Publication number | Publication date |
---|---|
EP1505263A1 (fr) | 2005-02-09 |
EP1651842A1 (fr) | 2006-05-03 |
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