US20130180246A1 - Diffuser for a gas turbine - Google Patents

Diffuser for a gas turbine Download PDF

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Publication number
US20130180246A1
US20130180246A1 US13/350,313 US201213350313A US2013180246A1 US 20130180246 A1 US20130180246 A1 US 20130180246A1 US 201213350313 A US201213350313 A US 201213350313A US 2013180246 A1 US2013180246 A1 US 2013180246A1
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US
United States
Prior art keywords
diffuser
inlet
outlet
wall
inner barrel
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.)
Abandoned
Application number
US13/350,313
Other languages
English (en)
Inventor
Deepesh Dinesh Nanda
Jonathan Glenn Luedke
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
Priority to US13/350,313 priority Critical patent/US20130180246A1/en
Assigned to GENERAL ELECTRIC COMPANY reassignment GENERAL ELECTRIC COMPANY ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: NANDA, DEEPESH DINESH, LUEDKE, JONATHAN GLENN
Priority to JP2013000768A priority patent/JP2013144979A/ja
Priority to EP13150586.9A priority patent/EP2615263A2/en
Priority to RU2013100408/06A priority patent/RU2013100408A/ru
Priority to CN2013100100984A priority patent/CN103206273A/zh
Publication of US20130180246A1 publication Critical patent/US20130180246A1/en
Abandoned 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
    • 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 turbines and, in particular, to diffusers for use with gas turbines and steam turbines.
  • Typical gas turbines include a diffuser cone, or diffuser, coupled to the last stage bucket of the rotor.
  • the diffuser serves, generally, to increase static pressure of the exhaust gas by decreasing the kinetic energy of the exhaust gas. Generally, this may be achieved by increasing the cross-sectional area of the diffuser in the direction of exhaust gas flow.
  • gas turbines are not operated at full load, but are designed for efficiency under such a full load. Therefore, part load performance efficiency is sacrificed, based on the full load design. Such inefficiencies are due, at least in part, to flow separation on the diffuser inner barrel, leading to tip strong flow profiles. Other factors, such as operation of the last stage of the turbine, may influence the flow profile. Additionally, flow passing over a center body of the diffuser generates large vortices that result in yet further system inefficiency.
  • a diffuser for a gas turbine includes an inlet adapted for coupling to the gas turbine.
  • the diffuser also includes at least one outlet located proximate a diffuser end, wherein the diffuser end is located downstream of the inlet.
  • the diffuser further includes an outer wall and an inner barrel extending substantially to the diffuser end.
  • an exhaust gas diffuser includes an inlet and an outlet.
  • the exhaust gas diffuser also includes an inner barrel extending from substantially the inlet to substantially the outlet.
  • the diffuser further includes an outer wall radially spaced apart from the inner barrel, wherein the outer wall and the inner barrel define a varying radius along a length of the diffuser between the inlet and the outlet.
  • a gas turbine includes a turbine casing that surrounds a portion of the gas turbine.
  • the gas turbine also includes an exhaust gas diffuser coupled to the turbine casing.
  • the diffuser includes an inlet adapted for coupling to the gas turbine, an outer wall, an inner barrel and a diffuser end downstream from the inlet, the inner barrel extending substantially to the diffuser end.
  • FIG. 1 is a side, cross-sectional view of a diffuser according to one aspect of the invention
  • FIG. 2 illustrates a flow profile associated with the diffuser illustrated in FIG. 1 ;
  • FIG. 3 illustrates a diffuser flow profile exhibiting flow separation
  • FIG. 1 illustrates one aspect of a diffuser 200 according to one embodiment of the present invention.
  • exhaust gas from the gas turbine flows through the diffuser 200 in the direction shown by arrow A.
  • an object is “downstream” of another object or location if it is displaced from it in the direction of arrow A and is “upstream” if it is displaced from it in a direction opposite of arrow A.
  • the diffuser 200 includes an inner barrel 202 that includes an inner wall 204 that forms an inner chamber 208 through which a portion of a rotor may pass.
  • the diffuser 200 includes an inlet 211 located proximate a diffuser entry end 210 and an outlet 220 located proximate a diffuser exit end 222 .
  • the inlet 211 may be coupled to a turbine, while the outlet 220 may be coupled to an adjacent object, such as a silencer.
  • the diffuser also includes an outer wall 206 radially spaced from the inner wall 204 of the inner barrel 202 . The area between the inner wall 204 and the outer wall 206 allows fluid or gas to flow downstream therethrough from the inlet 211 to the outlet 220 of the diffuser 200 .
  • the diffuser 200 may also include one or more struts 216 formed between the inner wall 204 and the outer wall 206 .
  • the strut 216 serves to hold the inner wall 204 and the outer wall 206 in a fixed relationship to one another, as well as providing bearing support.
  • the number of struts 216 is variable and commonly ranges from about four to about ten.
  • the inner wall 204 of the inner barrel 202 extends from the inlet 211 , or diffuser entry end 210 , to the outlet 220 , or diffuser exit end 222 .
  • the inner barrel 202 and hence the inner wall 204 , includes a first end 224 located proximate the inlet 211 and a second end 226 located proximate the outlet 220 and may take on numerous longitudinal contours as the inner barrel 202 extends from the first end 224 to the second end 226 .
  • the inner barrel 202 may slightly curve continuously from the first end 224 to the second end 226 , may curve slightly for only portions between the first end 224 and the second end 226 , may extend in a substantially straight direction, or may comprise segmented portions, where the overall longitudinal direction of the inner barrel 202 comprises any combination of the curvilinear paths described above. Irrespective of the shape of the inner barrel 202 , and more particularly the inner wall 204 , the inner barrel 202 and inner wall 204 extend to the diffuser outlet 220 or diffuser exit 222 .
  • the outer wall 206 includes a first portion 230 that extends from the inlet 211 , or diffuser entry end 210 , in a substantially downstream direction, as well as in a direction away from the inner wall 204 .
  • the sloping curvilinear direction of first portion 230 of the outer wall 206 terminates at an outer radius location 232 .
  • the outer wall 206 also includes a second portion 234 that extends from the outer radius location 232 in a substantially downstream direction to the outlet 220 , or diffuser exit end 222 .
  • the first portion 230 of the outer wall 206 angles away from the inner wall 204 more substantially than the second portion of the outer wall 206 , with the outer radius location 232 being located further upstream than a longitudinal midpoint 236 of the inner barrel 202 .
  • the portion of the inner barrel 202 located upstream of the longitudinal midpoint 236 is an inlet portion 238
  • the portion of the inner barrel located downstream of the longitudinal midpoint 236 is an outlet portion 240 . Therefore, the outer wall 206 is pushed to an outer radius further upstream than conventional diffuser outer wall constructions.
  • FIG. 2 shows a flow path profile in diffuser 200 shown in FIG. 1 .
  • the flow profile for the diffuser 200 of FIG. 1 is strong throughout the entire radial area of the diffuser 200 , even along the inner wall 204 .
  • the diffuser 200 reduces flow separation, thereby improving diffuser performance over a diffuser flow profile exhibiting flow separation, as shown in FIG. 3 .
  • the introduction of secondary air flow may be injected into the diffuser 200 .
  • Such a secondary air flow into the diffuser 200 and thereby a main diffuser flow alters overall flow by energizing a shear layer that is formed between the main flow and the inner wall 204 and/or outer wall 206 , causing a delay of the flow separation itself
  • the main flow widens and a larger static pressure recovery is achieved.
  • the inner wall 204 of the inner barrel 202 includes one or more actuator openings and one or more suction openings that are located downstream of the one or more actuator openings.
  • the suction opening allows common weak flow that passes directly over the inner wall 204 to enter the inner barrel 202 and pass through the flow manipulating device with sufficient force to exit the actuating opening in a manner that manipulates the flow profile of the diffuser 200 .
  • the manipulation of flow reduces flow separation, thereby increasing diffusion area.
  • diffuser 200 flow path is controlled by focusing the diffusion gradient near the region of high velocity and radially redistributing the flow.
  • the inner barrel 202 extends to the relative outlet 220 of the diffuser 200 .
  • an outer wall 206 of the diffuser 200 extends radially away from the inner barrel 202 at a rapid rate, starting upstream at the relative inlet 211 of the diffuser 200 . The result is a reduction in loss producing vortices associated with wake and a significant improvement in diffuser performance and thereby system heat rate gain. While the invention has been described in detail in connection with only a limited number of embodiments, it should be readily understood that the invention is not limited to such disclosed embodiments.

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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)
US13/350,313 2012-01-13 2012-01-13 Diffuser for a gas turbine Abandoned US20130180246A1 (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
US13/350,313 US20130180246A1 (en) 2012-01-13 2012-01-13 Diffuser for a gas turbine
JP2013000768A JP2013144979A (ja) 2012-01-13 2013-01-08 ガスタービン用ディフューザ
EP13150586.9A EP2615263A2 (en) 2012-01-13 2013-01-09 Diffuser for a gas turbine
RU2013100408/06A RU2013100408A (ru) 2012-01-13 2013-01-10 Диффузор для газовой турбины, диффузор для выхлопных газов и газовая турбина
CN2013100100984A CN103206273A (zh) 2012-01-13 2013-01-11 用于燃气涡轮机的扩压器

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/350,313 US20130180246A1 (en) 2012-01-13 2012-01-13 Diffuser for a gas turbine

Publications (1)

Publication Number Publication Date
US20130180246A1 true US20130180246A1 (en) 2013-07-18

Family

ID=47631262

Family Applications (1)

Application Number Title Priority Date Filing Date
US13/350,313 Abandoned US20130180246A1 (en) 2012-01-13 2012-01-13 Diffuser for a gas turbine

Country Status (5)

Country Link
US (1) US20130180246A1 (zh)
EP (1) EP2615263A2 (zh)
JP (1) JP2013144979A (zh)
CN (1) CN103206273A (zh)
RU (1) RU2013100408A (zh)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20160017734A1 (en) * 2013-03-29 2016-01-21 Mitsubishi Heavy Industries, Ltd. Axial flow rotating machine and diffuser
US20160230573A1 (en) * 2015-02-05 2016-08-11 Alstom Technology Ltd. Steam turbine diffuser configuration
US10563543B2 (en) 2016-05-31 2020-02-18 General Electric Company Exhaust diffuser

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2674845A (en) * 1951-05-02 1954-04-13 Walter D Pouchot Diffuser apparatus with boundary layer control
US3625630A (en) * 1970-03-27 1971-12-07 Caterpillar Tractor Co Axial flow diffuser
US5632142A (en) * 1995-02-15 1997-05-27 Surette; Robert G. Stationary gas turbine power system and related method
US5791136A (en) * 1994-08-23 1998-08-11 Hitachi, Ltd. Combined-cycle power generation plant, including a gas turbine, an annual exhaust gas channel having swirl suppression vanes, and a heat recovery boiler
US7272930B2 (en) * 2003-09-25 2007-09-25 Siemens Power Generation Exhaust diffuser assembly with tunable velocity profile
US20110088379A1 (en) * 2009-10-15 2011-04-21 General Electric Company Exhaust gas diffuser

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7493769B2 (en) * 2005-10-25 2009-02-24 General Electric Company Assembly and method for cooling rear bearing and exhaust frame of gas turbine

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2674845A (en) * 1951-05-02 1954-04-13 Walter D Pouchot Diffuser apparatus with boundary layer control
US3625630A (en) * 1970-03-27 1971-12-07 Caterpillar Tractor Co Axial flow diffuser
US5791136A (en) * 1994-08-23 1998-08-11 Hitachi, Ltd. Combined-cycle power generation plant, including a gas turbine, an annual exhaust gas channel having swirl suppression vanes, and a heat recovery boiler
US5632142A (en) * 1995-02-15 1997-05-27 Surette; Robert G. Stationary gas turbine power system and related method
US7272930B2 (en) * 2003-09-25 2007-09-25 Siemens Power Generation Exhaust diffuser assembly with tunable velocity profile
US20110088379A1 (en) * 2009-10-15 2011-04-21 General Electric Company Exhaust gas diffuser

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20160017734A1 (en) * 2013-03-29 2016-01-21 Mitsubishi Heavy Industries, Ltd. Axial flow rotating machine and diffuser
US20190234223A1 (en) * 2013-03-29 2019-08-01 Mitsubishi Heavy Industries, Ltd. Axial flow rotating machine and diffuser
US10753217B2 (en) * 2013-03-29 2020-08-25 Mitsubishi Heavy Industries, Ltd. Axial flow rotating machine and diffuser
US10760438B2 (en) * 2013-03-29 2020-09-01 Mitsubishi Heavy Industries, Ltd. Axial flow rotating machine and diffuser
US20160230573A1 (en) * 2015-02-05 2016-08-11 Alstom Technology Ltd. Steam turbine diffuser configuration
US10563543B2 (en) 2016-05-31 2020-02-18 General Electric Company Exhaust diffuser

Also Published As

Publication number Publication date
CN103206273A (zh) 2013-07-17
RU2013100408A (ru) 2014-07-20
JP2013144979A (ja) 2013-07-25
EP2615263A2 (en) 2013-07-17

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Legal Events

Date Code Title Description
AS Assignment

Owner name: GENERAL ELECTRIC COMPANY, NEW YORK

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:NANDA, DEEPESH DINESH;LUEDKE, JONATHAN GLENN;SIGNING DATES FROM 20120105 TO 20120113;REEL/FRAME:027533/0313

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION