EP3147460A1 - Axialturbine - Google Patents

Axialturbine Download PDF

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Publication number
EP3147460A1
EP3147460A1 EP15186492.3A EP15186492A EP3147460A1 EP 3147460 A1 EP3147460 A1 EP 3147460A1 EP 15186492 A EP15186492 A EP 15186492A EP 3147460 A1 EP3147460 A1 EP 3147460A1
Authority
EP
European Patent Office
Prior art keywords
turbine
stator
axial flow
radial tip
tip clearance
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Withdrawn
Application number
EP15186492.3A
Other languages
English (en)
French (fr)
Inventor
Carlos Simon-Delgado
Christian Sommer
Cyrille Bricaud
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.)
General Electric Technology GmbH
Original Assignee
General Electric Technology GmbH
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 General Electric Technology GmbH filed Critical General Electric Technology GmbH
Priority to EP15186492.3A priority Critical patent/EP3147460A1/de
Publication of EP3147460A1 publication Critical patent/EP3147460A1/de
Withdrawn legal-status Critical Current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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • 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
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/125—Fluid guiding means, e.g. vanes related to the tip of a stator vane
    • 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
    • F05D2240/307—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the tip of a rotor blade
    • 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
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved

Definitions

  • the present invention generally relates to an axial flow turbine crossed by an axial main flow and wherein a leakage flow, which typically passes through a radial tip clearance provided between a stator part and a rotor part, has an improved incidence when it merges with the main flow downstream the radial tip. In this way, aerodynamic losses are reduced and the energy conversion process is enhanced.
  • an axial flow turbine is made of a plurality of stages arranged through its axial development, each one comprising a stator part followed by a rotor part.
  • the stator parts include vanes which are fitted within a carrier, whilst the rotor parts include blades integral to a rotating shaft which is supported by the carrier.
  • the interaction between the hot gas axially flowing through the machine and the rotor parts causes the shaft to rotate.
  • the shaft rotation may then be utilized for the production of electrical energy of for the generation of a thrust in a jet engine of an aircraft. Due to the high speed rotation of the rotor shaft, a radial tip clearance is provided between stator parts and the rotor parts.
  • an axial flow turbine comprising a stator part and a rotor part between which a radial tip clearance is provided, wherein a main flow crosses the turbine and a leakage flow passes through the radial tip clearance during operation of the turbine, and wherein a deflector is arranged downstream the radial tip clearance and is configured to confer a swirl to the leakage flow.
  • the deflector is adapted to substantially align a direction of the leakage flow exiting the radial tip clearance to a direction of the main flow exiting the stator or rotor part.
  • the stator and/or the rotor part comprises one or more fins radially protruding within the clearance.
  • the axial flow turbine further comprises an abradable element disposed within the tip clearance facing the one or more fins and mounted on the stator part.
  • the one or more fins comprise a downstream fin located in the proximity of an exit of the radial tip clearance.
  • the deflector is arranged at the exit of the radial tip clearance in the proximity of the downstream fin.
  • the deflector is mounted on the stator part and the one or more fins are mounted on the rotor part.
  • the deflector is mounted on the rotor part and the one or more fins are mounted on the stator part.
  • the deflector comprises one or more deflecting elements equally positioned along a circumferential development of the stator part or the rotor part.
  • the one or more deflecting elements are airfoil-shaped.
  • Turbine 100 includes a vane carrier, generally indicated with numeral reference 21, to which a plurality of stator vanes 2 is integrally fitted.
  • Turbine 100 further includes a rotor shaft 31, to which a plurality of rotor blades 3 is connected.
  • a stator part 23 includes the stator vane 2, the vane carrier 21 and the necessary means for connecting the stator vane 2 to the vane carrier 21.
  • the stator part 23 includes a vane shroud 22 which is supported by the carrier 21.
  • a rotor part 33 includes the rotor blade 3, the rotor shaft 31 and the necessary means for connecting the rotor blade to the rotor shaft 31.
  • rotor part 33 also includes a rotor blade hub with platform and shank 32.
  • Turbine 100 comprises a plurality of stages, arranged along an axis A, each one made by a stator part 23 followed by a rotor part 33.
  • the stator vanes 2 are equally arranged along a circumferential development of the carrier 21, whilst the rotor blades 33 are arranged along a circumferential development of the rotor shaft 31.
  • FIG. 1 shows a schematic lateral section of the turbine 100 showing a first stage comprising a stator part 23 followed by a rotor part 33. It is also shown a stator vane 2 of a subsequent stage.
  • figure 1 shows along a central portion, a top section of the axial turbine 100, showing a row of airfoil-shaped stator vanes 2 followed by a row of airfoil-shaped rotor blades 3.
  • Stator vane 2 comprises a tip portion 24 which faces the rotor shaft 31.
  • a radial tip clearance 4 is provided between the stator vane 2 and the rotor shaft 31.
  • An abradable element 9 is located on the stator tip portion 24, in order to minimize the clearance 4.
  • the abradable element 9 can tolerate contact which may occur between the rotating shaft 31 and the stator vane 2.
  • an abradable element 9 is provided on the carrier 21 which faces a tip portion 34 of the rotor blade 3.
  • Turbine 100 is crossed, during operation, by a main flow of hot gas 5.
  • a portion of the main flow 5 leaks through the radial tip clearances 4 due to a favourable pressure gradient.
  • a leakage flow indicated with numeral reference 6 is not guided by the stator vanes 2 and does not receive the optimum swirl necessary to have the correct incidence when approaching the rotor blades 3.
  • fins 8 radially protruding into the radial tip clearances 4 are provided on the rotor shaft 31, facing the stator vane 2, and on the carrier 21 facing the rotor blades 3.
  • fins 8 comprise an upstream fin and a downstream fin, the latter being positioned in the proximity of an exit of the radial tip clearance 4, but it will be appreciated that only one fin may be provided in the tip clearance.
  • the presence of the fins 8 creates a barrier for preventing a leakage flow to go through the clearance 4, this way bypassing the stator parts 23 or the rotor parts 32.
  • the leakage flow 6 still passes through the clearance 4 creating the negative effect on the incidence of the main flow 5 approaching a stator vane 2 or a rotor blade 3, as above explained.
  • Turbine 1 differs from the turbine according to the prior art in that it comprises a deflector 7 which is arranged downstream the radial tip clearance 4, preferably in the proximity of an exit thereof, and it is configured to confer a swirl to the leakage flow 6. More in particular, with reference to the turbine stage here described, as clearly shown in the figure by the arrows of the main flow 5 and leakage flow 6, the deflector 7 located on the tip portion 24 of the stator vane 2 is adapted to substantially align a direction of the leakage flow 6 exiting the radial tip clearance 4 to a direction of the main flow 5 exiting the stator vanes row 2.
  • the deflector 7 located on the carrier 21 facing the rotor blade 3, is adapted to substantially align a direction of the leakage flow 6 exiting the radial tip clearance 4 to a direction of the main flow 5 exiting the rotor blades row 3.
  • the deflector 7 is arranged substantially at the exit of the radial tip clearance in the proximity of the downstream fin. The closer the deflector 7 is to the fin 8, then the better result is achieved in terms of conferring the wished swirl to the leakage flow before it joins the main flow 5.
  • the deflector 7 is mounted on the stator part 23, and specifically on the stator vane 2 and on the carrier 21, whilst the fins 8 are mounted on the rotor part 33, and respectively on the rotor shaft 31 and on the tip portion 34 of the rotor blade 34. It will be appreciated that, according to a variant of this embodiment, the deflector 7 may also be mounted on the rotor part 33, and specifically on the rotor shaft 31 and on the rotor blade 3, whilst the fins 8 may also be mounted on the stator part 23, and respectively on the tip portion 24 of the stator vane 2 and on the carrier 21.
  • figure 3 it is exemplary shown the radial tip clearance 4 formed between the stator vane 2 and the rotor shaft 31.
  • the deflector 7 is positioned in the proximity of the downstream fin 8 in a way to deflect the leakage flow 6.
  • figure 3 shows a bottom-to-top view along section line B-B'.
  • deflector 7 is visible as a plurality of deflecting elements 71 which are equally positioned along a circumferential development of the stator part 23.
  • deflecting elements 71 confer to the leakage flow lines 6 a swirl which is similar to the one operated by the stator vanes 2. In this way, when leakage flow 6 and the main flow 5 merge, they are substantially aligned and hence the incidence of the latter approaching the subsequent rotor blade row is effectively improved.
  • the deflecting elements 71 are airfoil-shaped.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP15186492.3A 2015-09-23 2015-09-23 Axialturbine Withdrawn EP3147460A1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP15186492.3A EP3147460A1 (de) 2015-09-23 2015-09-23 Axialturbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP15186492.3A EP3147460A1 (de) 2015-09-23 2015-09-23 Axialturbine

Publications (1)

Publication Number Publication Date
EP3147460A1 true EP3147460A1 (de) 2017-03-29

Family

ID=54196893

Family Applications (1)

Application Number Title Priority Date Filing Date
EP15186492.3A Withdrawn EP3147460A1 (de) 2015-09-23 2015-09-23 Axialturbine

Country Status (1)

Country Link
EP (1) EP3147460A1 (de)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3069276A1 (fr) * 2017-07-18 2019-01-25 Safran Aircraft Engines Ensemble d'etancheite pour turbomachine
WO2019131011A1 (ja) * 2017-12-28 2019-07-04 三菱重工航空エンジン株式会社 航空機用ガスタービン及び航空機用ガスタービンの動翼
CN114207252A (zh) * 2019-08-06 2022-03-18 赛峰飞机发动机公司 用于涡轮机涡轮并包括设有导向叶片的磨损面的可磨损部件
US11655723B2 (en) 2019-01-31 2023-05-23 Mitsubishi Heavy Industries, Ltd. Rotating machine

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US881474A (en) * 1906-08-14 1908-03-10 Belliss & Morcom Ltd Turbine-motor.
JPS578302A (en) * 1980-06-19 1982-01-16 Hitachi Ltd Internal stage structure of multistage axial-flow machine
GB2110767A (en) * 1981-11-27 1983-06-22 Rolls Royce A shrouded rotor for a gas turbine engine
DE3523469A1 (de) * 1985-07-01 1987-01-08 Bbc Brown Boveri & Cie Beruehrungsfreie spaltdichtung fuer turbomaschinen
WO2004113770A2 (en) * 2003-06-20 2004-12-29 Elliott Company Swirl-reversal abradable labyrinth seal
JP2007321721A (ja) * 2006-06-05 2007-12-13 Toshiba Corp 軸流タービン段落および軸流タービン
WO2011029420A1 (de) * 2009-09-10 2011-03-17 Mtu Aero Engines Gmbh Umlenkvorrichtung für einen leckagestrom in einer gasturbine und gasturbine
US20130189107A1 (en) * 2012-01-24 2013-07-25 General Electric Company Turbine Packing Deflector
US20130230379A1 (en) * 2012-03-01 2013-09-05 General Electric Company Rotating turbomachine component having a tip leakage flow guide

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US881474A (en) * 1906-08-14 1908-03-10 Belliss & Morcom Ltd Turbine-motor.
JPS578302A (en) * 1980-06-19 1982-01-16 Hitachi Ltd Internal stage structure of multistage axial-flow machine
GB2110767A (en) * 1981-11-27 1983-06-22 Rolls Royce A shrouded rotor for a gas turbine engine
DE3523469A1 (de) * 1985-07-01 1987-01-08 Bbc Brown Boveri & Cie Beruehrungsfreie spaltdichtung fuer turbomaschinen
WO2004113770A2 (en) * 2003-06-20 2004-12-29 Elliott Company Swirl-reversal abradable labyrinth seal
JP2007321721A (ja) * 2006-06-05 2007-12-13 Toshiba Corp 軸流タービン段落および軸流タービン
WO2011029420A1 (de) * 2009-09-10 2011-03-17 Mtu Aero Engines Gmbh Umlenkvorrichtung für einen leckagestrom in einer gasturbine und gasturbine
US20130189107A1 (en) * 2012-01-24 2013-07-25 General Electric Company Turbine Packing Deflector
US20130230379A1 (en) * 2012-03-01 2013-09-05 General Electric Company Rotating turbomachine component having a tip leakage flow guide

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3069276A1 (fr) * 2017-07-18 2019-01-25 Safran Aircraft Engines Ensemble d'etancheite pour turbomachine
WO2019131011A1 (ja) * 2017-12-28 2019-07-04 三菱重工航空エンジン株式会社 航空機用ガスタービン及び航空機用ガスタービンの動翼
JP2019120140A (ja) * 2017-12-28 2019-07-22 三菱重工航空エンジン株式会社 航空機用ガスタービン及び航空機用ガスタービンの動翼
US11339676B2 (en) 2017-12-28 2022-05-24 Mitsubishi Heavy Industries Aero Engines, Ltd. Aircraft gas turbine, and rotor blade of aircraft gas turbine
US11655723B2 (en) 2019-01-31 2023-05-23 Mitsubishi Heavy Industries, Ltd. Rotating machine
CN114207252A (zh) * 2019-08-06 2022-03-18 赛峰飞机发动机公司 用于涡轮机涡轮并包括设有导向叶片的磨损面的可磨损部件
US20220275731A1 (en) * 2019-08-06 2022-09-01 Safran Aircraft Engines Abradable member for a turbine of a turbomachine, comprising a wear face provided with guide vanes
CN114207252B (zh) * 2019-08-06 2024-05-24 赛峰飞机发动机公司 用于涡轮机涡轮并包括设有导向叶片的磨损面的可磨损部件
US11994032B2 (en) * 2019-08-06 2024-05-28 Safran Aircraft Engines Abradable member for a turbine of a turbomachine, comprising a wear face provided with guide vanes

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