EP1505263A1 - Dispositif de guidage dans un passage d'échappement pour une turbomachine et procédé d'opération - Google Patents
Dispositif de guidage dans un passage d'échappement pour une turbomachine et procédé d'opération Download PDFInfo
- Publication number
- EP1505263A1 EP1505263A1 EP03018164A EP03018164A EP1505263A1 EP 1505263 A1 EP1505263 A1 EP 1505263A1 EP 03018164 A EP03018164 A EP 03018164A EP 03018164 A EP03018164 A EP 03018164A EP 1505263 A1 EP1505263 A1 EP 1505263A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- guide blade
- trailing edge
- abströmleiteinrichtung
- rotation
- axis
- 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.)
- Withdrawn
Links
Images
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 a Abströmleit adopted in one Diffuser of a turbomachine with a baffle, the has a leading edge and a trailing edge between where a deflection is provided and the flow medium deflected from a direction of incidence and a method for changing a Abströmleit vibration.
- a gas turbine as an example of a turbomachine is compressed air in the compressor part and heated and then in a combustion chamber with admixture of a Fuel is heated and accelerated.
- a multi-level Turbine connects fluidically to the combustion chamber. Through the multi-stage turbine flows the flow medium, the a mixture of the burned fuel and the compressed one Air is. The movement of the flow medium generates an angular momentum on the rotor and thus eventually leads to a rotation of the rotor. The rotational energy is subsequently by means of a generator into electrical energy transformed.
- the bearing star serves on the one hand for deflecting the flow medium and on the other as a holder for the rotatably mounted rotor.
- the bearing star and especially the baffles rigid and made of the same material.
- Object of the present invention is to provide a Abströmleit boots indicate with the flow losses in one Diffuser can be reduced.
- Another task is to provide a method for changing a Abströmleit adopted in a diffuser to reduce the Specify flow losses.
- the task directed to the outflow device is solved by a Abströmleit adopted in a diffuser a turbomachine with a guide blade, the leading edge and an outflow edge has between them Deflection is provided, which is a flow medium deflects a direction of incidence, wherein the guide sheet in terms of a course of its deflection relative to the direction of incidence is adjustable.
- the task directed towards the method is solved by a method for changing a Abströmleit adopted 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, the one Flow medium deflects from an incident direction, wherein a Course of the deflection of the guide blade relative to Einfallsichtung is adjustable.
- the advantage is, inter alia, that a flow a flow medium through the Abströmleit raised can be selectively changed and thereby a flow of the Lagersterns is improved.
- Another advantage is that the Abströmleit worn during normal operation can be adjusted.
- Another advantage is that an exhaust gas swirl is reduced and furthermore, for each load condition of the turbine or Operating condition of the turbine improves the flow.
- the guide blade is formed such that the Turning is rotatable.
- the Leitblatt is around a rotation axis rotatably mounted.
- the axis of rotation runs here essentially perpendicular to the direction of incidence. Thereby is the Leitblattaerodynamik changed overall.
- the outer shape of the deflection surface is adjustable educated.
- the Leitblatt comprises a in the Leading edge located front part and one in the trailing edge located rear part.
- the located in the trailing edge Rear part is rotatably mounted about a rotation axis.
- the The axis of rotation is substantially parallel to the trailing edge educated. .
- the rear part is in a further embodiment the invention designed such that the rear part in a flow direction directly from the leading edge to the trailing edge, is moved.
- the length in the direction of flow a respective Leitblattes can thereby individually be changed.
- the Leitblatt be shortened or extended in the flow direction.
- FIG 1 is a perspective view of a Prior art gas turbine 1 can be seen.
- rotor 2 At one rotatably mounted rotor 2 is inter alia an end turbine stage 3, which includes a plurality of blades 4, mounted.
- the one Lower part 5a and an upper part 5b Around the rotor 2 around an outer housing is arranged, the one Lower part 5a and an upper part 5b has.
- the rotor 2 is in order a rotation axis 6 rotatably mounted.
- a flow medium flows in operation parallel to the axis of rotation 6 in the direction the turbine stage 3.
- the diffuser 7 After the diffuser 7 flows the flow medium under a direction of incidence by a So-called bearing star, which also serves as Abströmleit driving 8 referred to as.
- the Abströmleit prepared 8 comprises six guide blades 9. In alternative embodiments are less or more than six guide blades 9 possible.
- the flow medium flows at a varying outflow angle after the turbine stage 3 off.
- the outflow angle hangs from a load attached to the rotor 2.
- the Abströmleit driving 8 comprises a rotor-side end 10 and a stator-side end 11.
- the rotor-side end 10 is formed such that the rotor 2 rotatably supported therein becomes.
- FIG 2 is a perspective view of a Leitblatt 9 to see.
- a flow medium to the guide blade 9.
- the direction of arrival 12th depends on the outflow angle.
- the flow medium hits initially on a leading edge 13, flows around each of a deflection 15 and then flows from a trailing edge 14 out of the gas turbine 1 out.
- the guide blade 9 is formed such that the guide blade 9 with respect to a course of its deflection 15 is adjustable relative to the direction of incidence 12.
- the deflection surface (15) can be rotated be.
- the outer Shape of the deflection surface (15) to be adjustable.
- FIG. 3 shows a cross section of the guide blade 9.
- the viewing direction is in this case substantially perpendicular to the direction of incidence 12 in the direction of the axis of rotation 6.
- the guide blade 9 is in this case mounted rotatably about a rotation axis 16.
- This axis of rotation 16 is substantially perpendicular to the direction of incidence 12.
- the axis of rotation 16 is in this embodiment substantially in the middle of the guide blade 9.
- the axis of rotation 16 can also be attached in an alternative embodiment closer to the leading edge 13 or the trailing edge 14.
- the guide blade 9 is rotated about the axis of rotation 16.
- the guide blade 9 is thereby rotated about the axis of rotation 16 either clockwise 17 or counterclockwise 18.
- a flow medium, which impinges on the guide blade 9 in the direction of arrival 12, can be deflected thereby.
- FIG. 4 shows a second embodiment of the guide blade 9 to see.
- the guide blade 9 comprises in this embodiment a the leading edge 13 comprehensive front part 20 and a Trailing edge 14 comprehensive rear part 19.
- the front part 20 is rigid.
- the front part 20 can also be rotated about a further axis of rotation be stored.
- the rear part 19 is designed such that it is rotatably mounted about a rotation axis 21.
- the rotation axis 21 is in this case in a front region 22 of the rear part 19th appropriate.
- a rear portion 23 is thereby either the Clockwise 17 or counterclockwise 18 movable.
- FIG 5 is a third embodiment of the Leitblattes 9 to see.
- the rear part 19 in the flow direction either to the direction of incidence (represented by the Arrow 24) or against the direction of incidence (by the arrow 25).
- the front part 20 of the Leitblattes 9 can in another alternative embodiment to another Rotary axis are rotatably mounted.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Control Of Turbines (AREA)
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP03018164A EP1505263A1 (fr) | 2003-08-08 | 2003-08-08 | Dispositif de guidage dans un passage d'échappement pour une turbomachine et procédé d'opération |
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 |
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 (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
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 |
---|---|
EP1505263A1 true EP1505263A1 (fr) | 2005-02-09 |
Family
ID=33547671
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP03018164A Withdrawn EP1505263A1 (fr) | 2003-08-08 | 2003-08-08 | Dispositif de guidage dans un passage d'échappement pour une turbomachine et procédé d'opération |
EP04740600A Withdrawn EP1651842A1 (fr) | 2003-08-08 | 2004-07-02 | Dispositif de guidage dans un passage d'echappement pour une turbomachine et procede d'operation |
Family Applications After (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP04740600A Withdrawn EP1651842A1 (fr) | 2003-08-08 | 2004-07-02 | Dispositif de guidage dans un passage d'echappement pour une turbomachine et procede d'operation |
Country Status (2)
Country | Link |
---|---|
EP (2) | EP1505263A1 (fr) |
WO (1) | WO2005019604A1 (fr) |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1898055A2 (fr) | 2006-09-01 | 2008-03-12 | United Technologies Corporation | Aube statorique à géométrie variable pour un moteur à turbine à gaz |
EP2644838A1 (fr) * | 2012-03-27 | 2013-10-02 | Alstom Technology Ltd | Boîtier de gaz d'échappement d'une turbine à gaz |
EP2746535A1 (fr) * | 2012-12-20 | 2014-06-25 | General Electric Company | Conception de profil aérodynamique, à double rangée étagée, pour trame d'échappement de turbine à gaz |
CN103998725A (zh) * | 2011-12-14 | 2014-08-20 | 西门子能源有限公司 | 包括周向叶片的燃气涡轮发动机排气扩散器 |
EP3954875A3 (fr) * | 2020-08-04 | 2022-05-04 | MTU Aero Engines AG | Aube directrice, étage de compresseur, turbomachine et procédé pour exploiter une turbomachine |
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 WO PCT/EP2004/007252 patent/WO2005019604A1/fr not_active Application Discontinuation
- 2004-07-02 EP EP04740600A patent/EP1651842A1/fr not_active Withdrawn
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 |
Cited By (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1898055A2 (fr) | 2006-09-01 | 2008-03-12 | United Technologies Corporation | Aube statorique à géométrie variable pour un moteur à turbine à gaz |
EP1898055A3 (fr) * | 2006-09-01 | 2011-06-15 | United Technologies Corporation | Aube statorique à géométrie variable pour un moteur à turbine à gaz |
CN103998725A (zh) * | 2011-12-14 | 2014-08-20 | 西门子能源有限公司 | 包括周向叶片的燃气涡轮发动机排气扩散器 |
CN103998725B (zh) * | 2011-12-14 | 2016-05-25 | 西门子能源有限公司 | 包括周向叶片的燃气涡轮发动机排气扩散器 |
EP2644838A1 (fr) * | 2012-03-27 | 2013-10-02 | Alstom Technology Ltd | Boîtier de gaz d'échappement d'une turbine à gaz |
EP2746535A1 (fr) * | 2012-12-20 | 2014-06-25 | General Electric Company | Conception de profil aérodynamique, à double rangée étagée, pour trame d'échappement de 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 |
EP3954875A3 (fr) * | 2020-08-04 | 2022-05-04 | MTU Aero Engines AG | Aube directrice, étage de compresseur, turbomachine et procédé pour exploiter une turbomachine |
US11555500B2 (en) | 2020-08-04 | 2023-01-17 | MTU Aero Engines AG | Guide vane |
Also Published As
Publication number | Publication date |
---|---|
WO2005019604A1 (fr) | 2005-03-03 |
EP1651842A1 (fr) | 2006-05-03 |
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