EP2674572A2 - Turbinenabgasdiffusor - Google Patents

Turbinenabgasdiffusor Download PDF

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Publication number
EP2674572A2
EP2674572A2 EP13171438.8A EP13171438A EP2674572A2 EP 2674572 A2 EP2674572 A2 EP 2674572A2 EP 13171438 A EP13171438 A EP 13171438A EP 2674572 A2 EP2674572 A2 EP 2674572A2
Authority
EP
European Patent Office
Prior art keywords
strut
diffuser
extending
disposed
exhaust diffuser
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Withdrawn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
EP13171438.8A
Other languages
English (en)
French (fr)
Inventor
Moorthi Subramaniyan
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 Co
Original Assignee
General Electric Co
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 Co filed Critical General Electric Co
Publication of EP2674572A2 publication Critical patent/EP2674572A2/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Withdrawn legal-status Critical Current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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/145—Means for influencing boundary layers or secondary circulations
    • 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

Definitions

  • the subject matter disclosed herein relates to turbine systems, and more particularly to boundary layer flow control of turbine exhaust diffuser components.
  • Typical turbine systems such as gas turbine systems, for example, include an exhaust diffuser coupled to a turbine section of the turbine system to increase efficiency of a last stage bucket of the turbine section.
  • the exhaust diffuser is geometrically configured to rapidly decrease the kinetic energy of flow and increase static pressure recovery within the exhaust diffuser.
  • the exhaust diffuser is designed for full load operation, however, the turbine system is often operated at part load. Therefore, part load performance efficiency is sacrificed, based on the full load design.
  • Such inefficiency is due, at least in part, to flow separation on exhaust diffuser components, such as an inner barrel and radially extending struts, for example.
  • Flow separation often is caused, in part, by swirling of the flow upon exit of the last bucket stage of the turbine section and entry into the exhaust diffuser.
  • the magnitude of swirl may be quantified as a "tangential flow angle," and such an angle may be up to about 40 degrees, which leads to a higher angle of attack on the exhaust diffuser components, such as the radially extending struts, for example.
  • Such a flow characteristic leads to boundary layer growth and flow separation and eventually reduced pressure recovery.
  • a turbine exhaust diffuser includes a diffuser component disposed within the turbine exhaust diffuser and having an outer surface. Also included is a suction path extending between the outer surface and an interior compartment of the diffuser component, wherein the suction path is configured to ingest a fluid. Further included is an actuating path extending between the outer surface and the interior compartment of the diffuser component, wherein the actuating path is configured to expel the fluid. Yet further included is a flow manipulating device disposed within the interior compartment of the diffuser component.
  • a turbine exhaust diffuser includes a strut extending between, and operably coupled to, an annular inner barrel extending in a longitudinal direction of the turbine exhaust diffuser and an outer wall disposed radially outwardly from the inner barrel, the strut comprising a leading edge, a trailing edge and a suction side. Also included is a suction path extending from a first aperture in the suction side to an interior compartment of the strut. Further included is an actuating path extending from a second aperture in the suction side to the interior compartment of the strut. Yet further included is a flow manipulating device disposed within the interior compartment of the strut.
  • a turbine system includes a turbine casing that surrounds a portion of a turbine section of the turbine system. Also included is an exhaust diffuser that includes an inner barrel extending from proximate a diffuser inlet to a location downstream of the diffuser inlet. The exhaust diffuser also includes an outer wall disposed radially outwardly from the inner barrel. The exhaust diffuser further includes a strut extending between, and operably coupled to, the inner barrel and the outer wall, the strut comprising a leading edge, a trailing edge and a suction side.
  • the exhaust diffuser yet further includes a suction path extending from the suction side to an interior compartment of the strut and an actuating path extending from the suction side to the interior compartment of the strut.
  • the exhaust diffuser also includes a flow manipulating device disposed within the interior compartment of the strut.
  • a turbine system such as a gas turbine system, for example, is schematically illustrated with reference numeral 10.
  • the gas turbine system 10 includes a compressor section 12, a combustor section 14, a turbine section 16, a shaft 18 and a fuel nozzle 20. It is to be appreciated that one embodiment of the gas turbine system 10 may include a plurality of compressors 12, combustors 14, turbines 16, shafts 18 and fuel nozzles 20.
  • the compressor section 12 and the turbine section 16 are coupled by the shaft 18.
  • the shaft 18 may be a single shaft or a plurality of shaft segments coupled together to form the shaft 18.
  • the combustor section 14 uses a combustible liquid and/or gas fuel, such as natural gas or a hydrogen rich synthetic gas, to run the gas turbine system 10.
  • fuel nozzles 20 are in fluid communication with an air supply and a fuel supply 22.
  • the fuel nozzles 20 create an air-fuel mixture, and discharge the air-fuel mixture into the combustor section 14, thereby causing a combustion that creates a hot pressurized exhaust gas.
  • the combustor section 14 directs the hot pressurized gas through a transition piece into a turbine nozzle (or "stage one nozzle"), and other stages of buckets and nozzles causing rotation of turbine blades within an outer casing 24 of the turbine section 16. Subsequently, the hot pressurized gas is sent from the turbine section 16 to an exhaust diffuser 26 that is operably coupled to a portion of the turbine section, such as the outer casing 24, for example.
  • the exhaust diffuser 26 includes an inlet 28 configured to receive an exhaust fluid 30 from the turbine section 16.
  • An outlet 32 is disposed at a downstream location relative to the inlet 28.
  • Extending relatively axially along a longitudinal direction of the exhaust diffuser 26 at least partially between the inlet 28 and the outlet 32 is an inner barrel 34 that includes an outer surface 36.
  • the outer wall 38 is arranged in a relatively diverging configuration, such that kinetic energy of the exhaust fluid 30 is lessened subsequent to entering the inlet 28 of the exhaust diffuser 26. More particularly, a transfer of dynamic pressure to static pressure occurs within the exhaust diffuser 26 due to the diverging configuration of the outer wall 38.
  • the exhaust fluid 30 flows through the area defined by the outer surface 36 of the inner barrel 34 and the inner surface 40 of the outer wall 38.
  • a strut 42 disposed between the outer surface 36 of the inner barrel 34 and the inner surface 40 of the outer wall 38 .
  • the exhaust diffuser 26 typically includes a plurality of struts, with exemplary embodiments including a number of struts ranging from four (4) to twelve (12) struts.
  • the strut 42 serves to hold the inner barrel 34 and the outer wall 38 in a fixed relationship to one another, as well as providing bearing support. As the strut 42 is disposed within the area between the inner barrel 34 and the outer wall 38, the exhaust fluid 30 passes over the strut 42. Therefore, the strut 42 influences the flow characteristics of the exhaust fluid 30, and hence the overall exhaust diffuser performance.
  • the strut 42 is shaped as a cambered airfoil, and it is to be appreciated that the precise geometry and dimensions of the strut 42 may vary from that illustrated, based on the application.
  • the strut 42 includes a leading edge 44, a trailing edge 46, a suction side 48 and a pressure side 50. Extending from the leading edge 44 to the trailing edge 46 is an imaginary line referred to as a chord length 52.
  • a cambered airfoil shape it is to be understood that a generally symmetrical configuration may be employed.
  • the last stage bucket exit tangential flow angle (referred to herein as "swirl") of the exhaust fluid 30 increases based on the diverging configuration of the outer wall 38 of the exhaust diffuser 26, thereby leading to flow separation in regions proximate the outer surface 36 of the inner barrel 34, as well as regions proximate the various outer surfaces of the strut 42, such as the suction side 48 and the pressure side 50, for example.
  • a flow manipulating device 54 such as a rotating impeller, is disposed within the strut 42 to promote ingestion, or suction, of a portion of the exhaust fluid 30 passing over the suction side 48 of the strut 42 through a suction path 56.
  • the flow manipulating device 54 is generally fully enclosed by surrounding surfaces of the strut 42, with the exception of the suction path 56 and the actuating path 58.
  • the flow manipulating device 54 may be driven by various actuation structures, such as one or more motors.
  • the one or more motors may be mounted proximate the outer wall 38, the inner barrel 34, and/or the strut 42.
  • the suction path 56 extends from a first aperture 60 disposed within the suction side 48 of the strut 42 to an interior compartment 62 of the strut 42, where the flow manipulating device 54 is located.
  • the suction path 56 may be arranged at numerous angles, as the embodiment shown is merely for illustrative purposes only.
  • the first aperture 60, and therefore at least a portion of the suction path 56, is disposed proximate the leading edge 44 of the strut 42, however, it is contemplated that the first aperture 60 may be located substantially downstream of the leading edge 44.
  • the actuating path 58 extends from a second aperture 64 disposed within the suction side 48 of the strut 42 to the interior compartment 62.
  • the actuating path 58 may be arranged at numerous angles other than that illustrated.
  • the second aperture 64, and therefore at least a portion of the actuating path 58, may be disposed at various locations downstream of the first aperture 60.
  • the second aperture 64 is located about 60% downstream of the leading edge 44, with respect to the chord length 52 extending from the leading edge 44 to the trailing edge 46, however, the precise location may vary based on overall characteristics of the exhaust diffuser 26.
  • the first aperture 60 may be located proximate the trailing edge 46, rather than proximate the leading edge 44, as illustrated.
  • the actuating path 58 is disposed upstream of the suction path 56, such that the exhaust fluid 30 is ingested downstream and blown through the actuating path 58 to an upstream location.
  • the suction path 56 and the actuating path 58 are illustrated and described above as being disposed at locations between the suction side 48 and the interior compartment 62, it is also contemplated that the suction path 56 and the actuating path 58 may be disposed at locations between the pressure side 50 and the interior compartment 62 in other embodiments.
  • a plurality of suctions paths 56 and actuating paths 58 may be employed proximate both the suction side 48 and the pressure side 50.
  • the flow manipulating device 54 may be included within the inner barrel 34 to reduce flow separation and swirl proximate regions along the outer surface 36 of the inner barrel 34.
  • Such an embodiment is similar in structure and operation as that of an embodiment comprising the flow manipulating device 54 in the strut 42. Irrespective of whether the flow manipulating device 54 is included in the strut 42 or the inner barrel 34, or both, the flow manipulating device 54, used in conjunction with the suction path 56 and the actuating path 58, reduces flow separation proximate the outer surface 36 of the inner barrel 34 and the suction side 48 of the strut 42.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Supercharger (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP13171438.8A 2012-06-11 2013-06-11 Turbinenabgasdiffusor Withdrawn EP2674572A2 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/493,466 US20130330186A1 (en) 2012-06-11 2012-06-11 Turbine exhaust diffuser

Publications (1)

Publication Number Publication Date
EP2674572A2 true EP2674572A2 (de) 2013-12-18

Family

ID=48578881

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13171438.8A Withdrawn EP2674572A2 (de) 2012-06-11 2013-06-11 Turbinenabgasdiffusor

Country Status (5)

Country Link
US (1) US20130330186A1 (de)
EP (1) EP2674572A2 (de)
JP (1) JP2014013037A (de)
CN (1) CN103485847A (de)
RU (1) RU2013126500A (de)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3351753B1 (de) * 2016-02-09 2019-09-25 Mitsubishi Heavy Industries Compressor Corporation Gasexpander
CN114861272A (zh) * 2022-05-06 2022-08-05 中国华能集团清洁能源技术研究院有限公司 单桶多舱型桶型基础调平阶段临界吸力计算方法及***
US20240218809A1 (en) * 2022-12-30 2024-07-04 Pratt & Whitney Canada Corp. Engine strut flow control

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3082976A (en) * 1960-07-02 1963-03-26 Dornier Werke Gmbh Aircraft with ground effect landing gear
US3581569A (en) * 1969-11-28 1971-06-01 Avco Corp Mounting of fluidic temperature sensor in gas turbine engines
US20030150962A1 (en) * 2002-02-12 2003-08-14 Bela Orban Method for controlling and delaying the separation of flow from a solid surface by suction coupling (controlling separation by suction coupling, CSSC)
US6866479B2 (en) * 2003-05-16 2005-03-15 Mitsubishi Heavy Industries, Ltd. Exhaust diffuser for axial-flow turbine
US20070158503A1 (en) * 2006-01-12 2007-07-12 Burg Donald E Fluid dynamic foil with Coanda energizer
US7766280B2 (en) * 2007-05-29 2010-08-03 United Technologies Corporation Integral suction device with acoustic panel

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
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Also Published As

Publication number Publication date
CN103485847A (zh) 2014-01-01
JP2014013037A (ja) 2014-01-23
RU2013126500A (ru) 2014-12-20
US20130330186A1 (en) 2013-12-12

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