EP3392468B1 - Exhaust diffuser of a gas turbine engine having variable guide vane rings - Google Patents

Exhaust diffuser of a gas turbine engine having variable guide vane rings Download PDF

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Publication number
EP3392468B1
EP3392468B1 EP17193245.2A EP17193245A EP3392468B1 EP 3392468 B1 EP3392468 B1 EP 3392468B1 EP 17193245 A EP17193245 A EP 17193245A EP 3392468 B1 EP3392468 B1 EP 3392468B1
Authority
EP
European Patent Office
Prior art keywords
diffuser
exhaust
guide
vanes
struts
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.)
Active
Application number
EP17193245.2A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP3392468A1 (en
Inventor
Dae Hyun Kim
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.)
Doosan Heavy Industries and Construction Co Ltd
Original Assignee
Doosan Heavy Industries and Construction Co Ltd
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Filing date
Publication date
Application filed by Doosan Heavy Industries and Construction Co Ltd filed Critical Doosan Heavy Industries and Construction Co Ltd
Publication of EP3392468A1 publication Critical patent/EP3392468A1/en
Application granted granted Critical
Publication of EP3392468B1 publication Critical patent/EP3392468B1/en
Active legal-status Critical Current
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
    • 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
    • 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
    • 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
    • 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
    • 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
    • F05D2250/30—Arrangement of components
    • F05D2250/32—Arrangement of components according to their shape
    • F05D2250/324—Arrangement of components according to their shape divergent
    • 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
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/17—Purpose of the control system to control boundary layer

Definitions

  • the present invention relates to an exhaust diffuser and a gas turbine having the same and, more particularly, to an exhaust diffuser having variable vanes.
  • a gas turbine 10 comprises, as shown in FIG. 1 , a compressor 15, a combustor 25, and a turbine 40.
  • Air suctioned through an air inlet 20 is compressed into high-temperature and high-pressure compressed air by the compressor 15, high-temperature and high-pressure combustion gas (working fluid) is produced by combusting the compressed air by supplying fuel to the compressed air in the combustor 25, the turbine 40 is operated by the combustion gas, and a power generator connected to the compressor 15 is operated.
  • One of important aerodynamic problems during normal operation of a gas turbine engine 10 is to efficiently discharge combustion gas flowing out with high momentum through the last stage 60 of a turbine 40.
  • a radial diffuser may be used to guide combustion gas into the radial direction.
  • a radial diffuser 100' as shown in FIG. 2 , generally includes a plurality of struts 140' mounted on an internal diffuser guide 150' and surrounded by an external diffuser guide 130'.
  • the radial diffuser 100' changes the kinetic energy of the combustion gas flowing out through the last stage of the turbine into potential energy of increased static pressure. Increasing the entire restoration of static pressure increases the performance and efficiency of the entire gas turbine engine.
  • Patent Document 1 Korean Patent Application Publication No. 10-2015-0123950 (published on November 4, 2015 )
  • US 8776527 B1 discloses a discharge nozzle having a centerbody and a conduit enclosing the centerbody and is operable to receive exhaust flow from a turbine discharge of a gas turbine engine.
  • US2013265848 A1 discloses a duct having flow conducting surfaces, with a flow guide surface arranged in the duct.
  • the present invention describes an exhaust diffuser according to claim 1.
  • the performance of the exhaust diffuser is improved by controlling the profile of a velocity field at an inlet where exhaust gas flows into the exhaust diffuser, and a gas turbine having the exhaust diffuser.
  • the vanes may be concentrically mounted and form a ring-shaped structure when viewed in a longitudinal section.
  • Two or more vanes may be mounted at a predetermined distance from each other on the struts.
  • the vanes may have a streamline structure or an airfoil structure when viewed in a longitudinal section.
  • the struts may have a streamline structure or an airfoil structure when viewed in a longitudinal section.
  • a guide projection extending in a flow direction of exhaust gas is formed on an outer side of the vane.
  • the guide projection has a streamline structure continuing from the outer side of each vane when viewed in a longitudinal section.
  • a gas turbine engine having the features of claim 6 is provided.
  • the exhaust diffuser of the present invention since there are provided struts and rotary vanes that are formed in a specific structure, it is possible to effectively remove flow separation on the outer side of the internal diffuser guide by controlling the profile of a velocity field at an inlet where exhaust gas flows into the exhaust diffuser. Accordingly, it is possible to provide an exhaust diffuser of which performance is improved, and a gas turbine having the exhaust diffuser.
  • the exhaust diffuser of the present invention since the exhaust diffuser includes three or more struts spaced at a predetermined angle from each other around the outer side of the internal diffuser guide and vanes connecting adjacent struts and formed in a ring shape in a cross-section, it is possible to easily control radial inlet flow generated in an operation area. Accordingly, it is possible to improve performance of the exhaust diffuser by controlling the profile of a velocity field at an inlet where exhaust gas flows into the exhaust diffuser.
  • the vanes and the struts have a streamline structure of an airfoil structure, it is possible to easily control the profile of a velocity field at an inlet of exhaust gas flowing in the exhaust diffuser.
  • the exhaust diffuser of the present invention since a guide projection is formed on the outer side of each vane, it is possible to effectively control the profile of a velocity field at an inlet of exhaust gas flowing in the exhaust diffuser.
  • FIG. 3 is a perspective view showing an exhaust diffuser according to an embodiment of the present invention and FIG. 4 is a cross-sectional view showing the exhaust diffuser according to an embodiment of the present invention.
  • an exhaust diffuser 100 includes a hollow cylindrical internal diffuser guide 101 and an external diffuser guide 102 and further includes struts 110 and a rotary vane 120.
  • the struts 110 and the rotary vane 120 that have a specific structure, it is possible to effectively remove flow separation on the outer side of the internal diffuser guide 101 by controlling the profile of a velocity field at an inlet of exhaust gas flowing in the exhaust diffuser 100. Accordingly, it is possible to provide variable guide vanes that can improve performance of a diffuser, and a gas turbine having the vanes.
  • the struts 110 are disposed between the internal diffuser guide 101 and the external diffuser guide 102 to space the internal diffuser guide 101 and the external diffuser guide 102 at a predetermined distance.
  • the struts 110 may have a streamline structure or an airfoil structure when viewed in a longitudinal section.
  • a specific number of struts 110 are shown in FIG. 3 , but the number may be appropriately changed different from that shown in the figure in consideration of a pressure drop of the exhaust gas flowing in the exhaust diffuser 100.
  • the vanes 120 surround the outer side of the internal diffuser guide 101 and are rotatably mounted on the struts 110. As shown in FIG. 3 , two or more vanes 120 may be mounted on the struts 110 at predetermined distance from each other.
  • the vanes 120 are formed in a ring shape surrounding the internal diffuser guide 101.
  • the number and position of the vanes 120 may be appropriately changed in consideration of a pressure drop of the exhaust gas flowing in the exhaust diffuser 100.
  • Three or more struts 110 may be spaced at a predetermined angle around the outer side of the internal diffuser guide 101.
  • the vanes 120 connect adjacent struts 110 and may be formed to correspond to the outer side of the internal diffuser guide 101.
  • the vanes 120 may be sequentially mounted to form a ring-shaped structure when viewed in a longitudinal section.
  • FIG. 5 is a partial enlarged view showing a strut 110, a vane 120, and a driving unit 111 according to an embodiment of the present invention.
  • the vane 120 according to the embodiment is mounted on the strut 110 through a hinge unit 121.
  • the driving unit 111 that operates with the hinge unit 121 of the vane 120 through a link 112 is disposed inside the strut 110.
  • the link 112 is moved by forward and backward rotation of the driving unit 111, so the vane 120 mounted through the hinge unit 121 is rotated clockwise or counterclockwise in the figures. That is, the angle of the vane 120 to flow of exhaust gas is changed by the hinge unit 121 and the link 112.
  • FIG. 6 is a perspective view showing a vane and a guide projection according to another embodiment of the present invention and FIG. 7 is a cross-sectional view showing the vane and the guide projection shown in FIG. 6 .
  • a guide projection 122 extending in the flow direction of exhaust gas is formed on an outer side of the vane 120 according to the embodiment.
  • the guide projection 122 forms a streamline shape continuing from the outer side of the vane 120 when viewed in the longitudinal section. Since the guide projection 122 is positioned on the vane 120 in the flow direction of exhaust gas flowing, the exhaust gas splits to the left and right of the guide projection 122. As the exhaust gas is split by the guide projection 122, it is possible to suppress flow separation that is promoted by the viscosity of surrounding exhaust gas. Accordingly, the guide projection 122 contributes to controlling the profile of a velocity field of the exhaust gas at an inlet.
  • guide projection 122 is shown on one vane 120 in the figures, several guide projections 122 may be provided on one vane 120. In order to form a plurality of guide projections 122, it may be considered to make the gaps between the guide projections 122 different in consideration of the profile of the exhaust gas.
  • the exhaust diffuser of the present invention since there are provided struts and rotary vanes that are formed in a specific structure, it is possible to effectively remove flow separation on the outer side of the internal diffuser guide by controlling the profile of a velocity field at an inlet where exhaust gas flows into the exhaust diffuser. Accordingly, it is possible to provide an exhaust diffuser of which performance is improved, and a gas turbine having the exhaust diffuser.
  • the exhaust diffuser of the present invention since the exhaust diffuser includes three or more struts spaced at a predetermined angle from each other around the outer side of the internal diffuser guide and vanes connecting adjacent struts and formed in a ring shape when viewed in a longitudinal section, it is possible to easily control radial inlet flow generated in an operation area. Accordingly, it is possible to improve performance of the exhaust diffuser by controlling the profile of a velocity field at an inlet where exhaust gas flows into the exhaust diffuser.
  • the vanes and the struts have a streamline structure of an airfoil structure, it is possible to easily control the profile of a velocity field at an inlet of exhaust gas flowing in the exhaust diffuser.
  • the exhaust diffuser of the present invention since a guide projection is formed on the outer side of each vane, it is possible to easily control the profile of a velocity field at an inlet of exhaust gas flowing in the exhaust diffuser.
  • the present invention can also provide a gas turbine having the exhaust diffuser 100 of the present invention, so it is possible to improve performance of the exhaust diffuser by controlling the profile of a velocity field at an inlet where exhaust gas flows into the exhaust diffuser. Accordingly, it is possible to provide a gas turbine of which performance is improved.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Supercharger (AREA)
EP17193245.2A 2017-04-18 2017-09-26 Exhaust diffuser of a gas turbine engine having variable guide vane rings Active EP3392468B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
KR1020170049791A KR101902240B1 (ko) 2017-04-18 2017-04-18 가변형 가이드 베인을 포함하는 배기 디퓨저 및 이를 포함하는 가스터빈

Publications (2)

Publication Number Publication Date
EP3392468A1 EP3392468A1 (en) 2018-10-24
EP3392468B1 true EP3392468B1 (en) 2020-06-10

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP17193245.2A Active EP3392468B1 (en) 2017-04-18 2017-09-26 Exhaust diffuser of a gas turbine engine having variable guide vane rings

Country Status (4)

Country Link
US (1) US20180298785A1 (ja)
EP (1) EP3392468B1 (ja)
JP (1) JP6475802B2 (ja)
KR (1) KR101902240B1 (ja)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11753997B2 (en) * 2020-03-26 2023-09-12 Hamilton Sundstrand Corporation Exhaust baffle component for an air turbine assembly
CN114719290B (zh) * 2022-03-17 2023-03-31 西北工业大学 一种放气方案可调的扩压器结构及应用

Family Cites Families (16)

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Publication number Priority date Publication date Assignee Title
US3012709A (en) * 1955-05-18 1961-12-12 Daimler Benz Ag Blade for axial compressors
US4175640A (en) * 1975-03-31 1979-11-27 Boeing Commercial Airplane Company Vortex generators for internal mixing in a turbofan engine
CA1038298A (en) * 1975-10-14 1978-09-12 John Korta Adjustable vane assembly for a gas turbine
US4215536A (en) * 1978-12-26 1980-08-05 The Boeing Company Gas turbine mixer apparatus
US5813828A (en) * 1997-03-18 1998-09-29 Norris; Thomas R. Method and apparatus for enhancing gas turbo machinery flow
US6792758B2 (en) * 2002-11-07 2004-09-21 Siemens Westinghouse Power Corporation Variable exhaust struts shields
EP2153051A4 (en) * 2007-05-22 2013-06-19 Volvo Aero Corp MASKING ARRANGEMENT FOR GAS TURBINE ENGINE
JP2009036118A (ja) * 2007-08-02 2009-02-19 Mitsubishi Heavy Ind Ltd 軸流排気型タービン
US8776527B1 (en) * 2008-06-17 2014-07-15 Rolls-Royce North American Technologies, Inc. Techniques to reduce infrared detection of a gas turbine engine
EP2577071B1 (de) * 2010-06-01 2017-12-20 Esg Mbh Kanal mit strömungsleitfläche
JP5951187B2 (ja) * 2011-03-29 2016-07-13 三菱重工業株式会社 タービン排気構造及びガスタービン
US9032721B2 (en) * 2011-12-14 2015-05-19 Siemens Energy, Inc. Gas turbine engine exhaust diffuser including circumferential vane
US9359900B2 (en) * 2012-10-05 2016-06-07 General Electric Company Exhaust diffuser
US9644496B2 (en) 2013-03-13 2017-05-09 General Electric Company Radial diffuser exhaust system
US20140314549A1 (en) * 2013-04-17 2014-10-23 General Electric Company Flow manipulating arrangement for a turbine exhaust diffuser
US10087824B2 (en) * 2015-02-25 2018-10-02 Garrett Transportation 1 Inc. Wastegate with injected flow

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Also Published As

Publication number Publication date
JP6475802B2 (ja) 2019-02-27
US20180298785A1 (en) 2018-10-18
KR101902240B1 (ko) 2018-09-28
EP3392468A1 (en) 2018-10-24
JP2018178986A (ja) 2018-11-15

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