US20130243564A1 - Exhaust diffuser for turbine - Google Patents

Exhaust diffuser for turbine Download PDF

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Publication number
US20130243564A1
US20130243564A1 US13/419,860 US201213419860A US2013243564A1 US 20130243564 A1 US20130243564 A1 US 20130243564A1 US 201213419860 A US201213419860 A US 201213419860A US 2013243564 A1 US2013243564 A1 US 2013243564A1
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United States
Prior art keywords
angle
turbine
guide surface
exhaust
last stage
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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
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US13/419,860
Inventor
Prakash Bavanjibhai Dalsania
Joseph Anthony Cotroneo
Sudhakar Neeli
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General Electric Co
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General Electric Co
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Publication date
Application filed by General Electric Co filed Critical General Electric Co
Priority to US13/419,860 priority Critical patent/US20130243564A1/en
Assigned to GENERAL ELECTRIC COMPANY reassignment GENERAL ELECTRIC COMPANY ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: Dalsania, Prakash Bavanjibhai, Neeli, Sudhakar, COTRONEO, JOSEPH ANTHONY
Priority to JP2013042473A priority patent/JP2013189975A/en
Priority to RU2013111162/06A priority patent/RU2013111162A/en
Priority to EP13158914.5A priority patent/EP2639404A1/en
Priority to CN2013100811952A priority patent/CN103306754A/en
Publication of US20130243564A1 publication Critical patent/US20130243564A1/en
Abandoned legal-status Critical Current

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    • 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
    • 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
    • F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
    • F01D5/143—Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
    • 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
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles

Definitions

  • the present invention relates to an exhaust diffuser for a turbine and to methods for reducing flow separation with over tip leakage flow with shrouded and unshrouded last stage buckets of the turbine.
  • Diffusers are commonly employed in steam turbines. Effective diffusers can improve turbine efficiency and output. Unfortunately, the complicated flow patterns existing in such turbines as well as the design problems caused by space limitations make fully effective diffusers almost impossible to design. A frequent result is flow separation that fully or partially destroys the ability of the diffuser to raise the static pressure as the steam velocity is reduced by increasing the flow area. For downward exhaust hoods used with axial steam turbines, the loss from the diffuser discharge to the exhaust hood discharge varies from top to bottom. At the top, much of the flow must be turned 180° to place it over the diffuser and inner casing, then turned downward. Pressure at the top is thus higher than at the sides, which are in turn higher than at the bottom.
  • an exhaust diffuser for a turbine comprises an inlet configured to receive exhaust gas from a last stage bucket of the turbine; and an exhaust gas guide surface configured to guide the exhaust gas.
  • a curvature of the guide surface comprises a first angle with respect to an axis of the turbine and a ratio of a guide surface axial length to the active length of the last stage bucket which is between about 0.45 to 0.70.
  • a method of diffusing exhaust of a turbine comprises energizing a boundary layer along a curved exhaust flow guide surface of an exhaust diffuser with over tip leakage of a last stage bucket of the turbine.
  • the curved exhaust flow guide surface is at a first angle with respect to an axis of the turbine and a ratio of a guide surface axial length to the active length of the last stage bucket which is between about 0.45 to 0.70.
  • FIG. 1 schematically depicts first and second exhaust flow diffusers in relation to a last stage bucket of a turbine
  • FIG. 2 schematically depicts the steam guide length of the second exhaust flow diffuser of FIG. 1 in relation to the last stage bucket;
  • FIG. 3 schematically depicts the angles of the steam guide surface of the second exhaust flow diffuser of FIG. 1 ;
  • FIG. 4 schematically depicts the angles of the steam guide surface in relation to an inclined shroud
  • FIG. 5 schematically depicts the last stage bucket and inclined shroud.
  • a first exhaust flow diffuser 2 of a steam turbine low pressure section includes an inlet 18 that receives steam passing a last stage bucket 14 of the turbine.
  • the exhaust flow diffuser 2 further includes a steam guide surface 4 that guides the steam flow passing from the last stage bucket 14 , and a diffuser end wall 6 .
  • a ratio of the axial length L of the diffuser (as measured from a centerline 16 of the last stage bucket 14 to the diffuser end wall 6 ) to the active length AL of the last stage bucket 14 is approximately 2.0.
  • the centerline 16 of the last stage bucket 14 is a radial line passing through the center of gravity of the bucket's root section.
  • a diffuser 8 of a second, different configuration from the diffuser 2 is also shown.
  • the diffuser 8 has a ratio of axial length L (as measured from the centerline 16 to the diffuser end wall 12 ) to active length AL of the last stage bucket 14 of approximately 1.35.
  • the first diffuser 2 and the second diffuser 8 have the same diffuser area ratio which results in the second diffuser 8 having a sharper steam guide surface 10 curvature. Maintaining the diffuser area ratio of the second diffuser 8 the same as the first diffuser may lead to a flow separation from the steam guide surface 10 due to higher curvature.
  • the diffuser 8 uses over tip leakage from the last stage bucket 14 to energize a boundary layer along the steam guide surface 10 of the diffuser 8 to reduce, or prevent, separation of the steam from the steam guide surface 10 . Reducing, or preventing, separation of the steam from the steam guide surface 10 improves the static pressure recovery.
  • the tip clearance of the last stage bucket 14 may be reduced, or minimized, to increase, or maximize, the work of the fluid (e.g., steam or hot gases) on the rotating blades of the turbine. Some amount of clearance may be provided to reduce the possibility of rub between the blades and the inner casing.
  • the last stage bucket 14 may have a hot radial tip clearance that varies between, for example, about 125 to 200 mils and the leakage flow rate for example, about 0.5% to 2% of the annulus flow rate. It should be appreciated that the tip clearance of the last stage bucket 14 may be otherwise, for example between about 50 to 160 mils.
  • the diffuser 8 having a L/AL ratio of approximately 1.5 has a ratio of the steam guide axial length SGL (as measured from the centerline 16 of the last stage bucket 14 to the end of the steam guide surface 10 ) to the active length AL of the last stage bucket 14 of approximately 0.45 to 0.70, for example approximately 0.55.
  • the last stage bucket 14 has a tip angle A of, for example, about 0° and the curvature of the steam guide surface 10 may have a first angle B that may correspond to a range of change in the angle over the previous 25% meridional length of the steam guide from the bucket tip slope, for example, 0° to 18°, for example about 2°, 11°, or 14°.
  • the second angle C of curvature of the steam guide surface 10 at the 50% meridional distance may be, for example, a change of 14° to 32°, for example about 20°, 22°, or 28°.
  • the third angle D of the curvature of the steam guide surface 10 at the 75% meridional distance may be, for example, a change of about 16° to 32°, for example about 24°, 26°, or 28°.
  • the turbine may include an inclined shroud 20 .
  • the last stage bucket 14 has a tip angle A of, for example, about 25° and the curvature of the steam guide surface 10 may have a first angle B that may correspond to a range of change in the angle over the previous 25% meridional length of the steam guide from the bucket tip slope, for example, 0° to 18°, for example about 2°, 11°, or 14°.
  • the second angle C of curvature of the steam guide surface 10 at the 50% meridional distance may be, for example, a change of 14° to 32°, for example about 20°, 22°, or 28°.
  • the third angle D of the curvature of the steam guide surface 10 at the 75% meridional distance may be, for example, a change of about 16° to 32°, for example about 24°, 26°, or 28°.

Abstract

An exhaust diffuser for a turbine includes an inlet configured to receive exhaust gas from a last stage bucket of the turbine and an exhaust gas guide surface configured to guide the exhaust gas. A curvature of the guide surface comprises a first angle with respect to an axis of the turbine and a ratio of a guide surface axial length to the active length of the last stage bucket which is between about 0.45 to 0.70. A method of diffusing exhaust of a turbine includes energizing a boundary layer along a curved exhaust flow guide surface of an exhaust diffuser with over tip leakage of a last stage bucket of the turbine.

Description

  • The present invention relates to an exhaust diffuser for a turbine and to methods for reducing flow separation with over tip leakage flow with shrouded and unshrouded last stage buckets of the turbine.
    • BACKGROUND OF THE INVENTION
  • In the discharge of exhaust steam from an axial flow turbine, for example discharge of this exhaust steam to a condenser, it is desirable to provide as smooth a flow of steam as possible and to minimize energy losses from accumulation of vortices, turbulences and non-uniformity in such flow. Usually the exhaust from the turbine is directed into an exhaust hood and from there through a discharge opening in the hood in a direction essentially normal to the axis of the turbine into a condenser. It is desirable to achieve a smooth transition from axial flow at the exhaust of the turbine to radial flow in the exhaust hood and thence a smooth flow at the discharge opening of this hood into the condenser.
  • In the constructing of an effective exhaust hood for use with such an axial flow turbine it is desirable to avoid acceleration losses within any guide means employed therein and to achieve a relatively uniform flow distribution at the discharge opening of the exhaust hood for the most efficient conversion of energy in the turbine and effective supplying of exhaust steam to the condenser to which it is connected.
  • It is also desirable to achieve optimum efficiency at the last stage buckets of the turbine prior to exhaust from the turbine by achieving a relatively uniform circumferential and radial pressure distribution in the exit plane of the last stage buckets. Usually, attempts have been made to accomplish these results while employing a hood having as short an axial length as possible, so as to limit the axial size of the turbine train.
  • Diffusers are commonly employed in steam turbines. Effective diffusers can improve turbine efficiency and output. Unfortunately, the complicated flow patterns existing in such turbines as well as the design problems caused by space limitations make fully effective diffusers almost impossible to design. A frequent result is flow separation that fully or partially destroys the ability of the diffuser to raise the static pressure as the steam velocity is reduced by increasing the flow area. For downward exhaust hoods used with axial steam turbines, the loss from the diffuser discharge to the exhaust hood discharge varies from top to bottom. At the top, much of the flow must be turned 180° to place it over the diffuser and inner casing, then turned downward. Pressure at the top is thus higher than at the sides, which are in turn higher than at the bottom.
    • BRIEF DESCRIPTION OF THE INVENTION
  • According to an exemplary embodiment, an exhaust diffuser for a turbine comprises an inlet configured to receive exhaust gas from a last stage bucket of the turbine; and an exhaust gas guide surface configured to guide the exhaust gas. A curvature of the guide surface comprises a first angle with respect to an axis of the turbine and a ratio of a guide surface axial length to the active length of the last stage bucket which is between about 0.45 to 0.70.
  • According to another exemplary embodiment, a method of diffusing exhaust of a turbine comprises energizing a boundary layer along a curved exhaust flow guide surface of an exhaust diffuser with over tip leakage of a last stage bucket of the turbine. The curved exhaust flow guide surface is at a first angle with respect to an axis of the turbine and a ratio of a guide surface axial length to the active length of the last stage bucket which is between about 0.45 to 0.70.
    • BRIEF DESCRIPTION OF THE DRAWINGS
  • FIG. 1 schematically depicts first and second exhaust flow diffusers in relation to a last stage bucket of a turbine;
  • FIG. 2 schematically depicts the steam guide length of the second exhaust flow diffuser of FIG. 1 in relation to the last stage bucket;
  • FIG. 3 schematically depicts the angles of the steam guide surface of the second exhaust flow diffuser of FIG. 1;
  • FIG. 4 schematically depicts the angles of the steam guide surface in relation to an inclined shroud; and
  • FIG. 5 schematically depicts the last stage bucket and inclined shroud.
    •  DETAILED DESCRIPTION OF THE INVENTION
  • Referring to FIG. 1, a first exhaust flow diffuser 2 of a steam turbine low pressure section includes an inlet 18 that receives steam passing a last stage bucket 14 of the turbine. The exhaust flow diffuser 2 further includes a steam guide surface 4 that guides the steam flow passing from the last stage bucket 14, and a diffuser end wall 6. A ratio of the axial length L of the diffuser (as measured from a centerline 16 of the last stage bucket 14 to the diffuser end wall 6) to the active length AL of the last stage bucket 14 is approximately 2.0. The centerline 16 of the last stage bucket 14 is a radial line passing through the center of gravity of the bucket's root section.
  • Referring still to FIG. 1, a diffuser 8 of a second, different configuration from the diffuser 2 is also shown. The diffuser 8 has a ratio of axial length L (as measured from the centerline 16 to the diffuser end wall 12) to active length AL of the last stage bucket 14 of approximately 1.35. As shown in FIG. 1, the first diffuser 2 and the second diffuser 8 have the same diffuser area ratio which results in the second diffuser 8 having a sharper steam guide surface 10 curvature. Maintaining the diffuser area ratio of the second diffuser 8 the same as the first diffuser may lead to a flow separation from the steam guide surface 10 due to higher curvature.
  • The diffuser 8 uses over tip leakage from the last stage bucket 14 to energize a boundary layer along the steam guide surface 10 of the diffuser 8 to reduce, or prevent, separation of the steam from the steam guide surface 10. Reducing, or preventing, separation of the steam from the steam guide surface 10 improves the static pressure recovery.
  • The tip clearance of the last stage bucket 14 may be reduced, or minimized, to increase, or maximize, the work of the fluid (e.g., steam or hot gases) on the rotating blades of the turbine. Some amount of clearance may be provided to reduce the possibility of rub between the blades and the inner casing. The last stage bucket 14 may have a hot radial tip clearance that varies between, for example, about 125 to 200 mils and the leakage flow rate for example, about 0.5% to 2% of the annulus flow rate. It should be appreciated that the tip clearance of the last stage bucket 14 may be otherwise, for example between about 50 to 160 mils.
  • Referring to FIG. 2, the diffuser 8 having a L/AL ratio of approximately 1.5 has a ratio of the steam guide axial length SGL (as measured from the centerline 16 of the last stage bucket 14 to the end of the steam guide surface 10) to the active length AL of the last stage bucket 14 of approximately 0.45 to 0.70, for example approximately 0.55. Referring to FIG. 3, the last stage bucket 14 has a tip angle A of, for example, about 0° and the curvature of the steam guide surface 10 may have a first angle B that may correspond to a range of change in the angle over the previous 25% meridional length of the steam guide from the bucket tip slope, for example, 0° to 18°, for example about 2°, 11°, or 14°. The second angle C of curvature of the steam guide surface 10 at the 50% meridional distance may be, for example, a change of 14° to 32°, for example about 20°, 22°, or 28°. The third angle D of the curvature of the steam guide surface 10 at the 75% meridional distance may be, for example, a change of about 16° to 32°, for example about 24°, 26°, or 28°.
  • Referring to FIGS. 4 and 5, the turbine may include an inclined shroud 20. The last stage bucket 14 has a tip angle A of, for example, about 25° and the curvature of the steam guide surface 10 may have a first angle B that may correspond to a range of change in the angle over the previous 25% meridional length of the steam guide from the bucket tip slope, for example, 0° to 18°, for example about 2°, 11°, or 14°. The second angle C of curvature of the steam guide surface 10 at the 50% meridional distance may be, for example, a change of 14° to 32°, for example about 20°, 22°, or 28°. The third angle D of the curvature of the steam guide surface 10 at the 75% meridional distance may be, for example, a change of about 16° to 32°, for example about 24°, 26°, or 28°.
  • Although the embodiments have been described with respect to a steam turbine, it should be appreciated that the diffuser may be used with gas turbines.
  • While the invention has been described in connection with what is presently considered to be the most practical and preferred embodiments, it is to be understood that the invention is not to be limited to the disclosed embodiments, but on the contrary, is intended to cover various modifications and equivalent arrangements included within the spirit and scope of the appended claims.

Claims (20)

What is claimed is:
1. An exhaust diffuser for a turbine, comprising:
an inlet configured to receive exhaust gas from a last stage bucket of the turbine; and
an exhaust gas guide surface configured to guide the exhaust gas, wherein a curvature of the guide surface comprises a first angle with respect to an axis of the turbine and a ratio of a guide surface axial length to the active length of the last stage bucket which is between about 0.45 to 0.70.
2. An exhaust diffuser according to claim 1, wherein a ratio of the guide surface axial length to the active length is about 0.55.
3. An exhaust diffuser according to claim 1, wherein a ratio of an axial length of the exhaust diffuser to the active length is between about 1.35 and 2.0.
4. An exhaust diffuser according to claim 1, wherein the curvature of the guide surface comprises a second angle and a third angle, and the first, second and third angles correspond to a range of change in the angle over the previous 25% meridional length of the steam guide at 25%, 50% and 75% meridional distances, respectively.
5. An exhaust diffuser according to claim 4, wherein the first angle change is in the range of 0° to 18°, the second angle change is in the range of 14° to 32°, and the third angle change is in the range of 16° to 32°.
6. An exhaust diffuser according to claim 4, wherein the second angle is larger than the first angle and the third angle is larger than the second angle.
7. An exhaust diffuser according to claim 4, wherein the second angle and the third angle are approximately equal.
8. An exhaust diffuser according to claim 4, wherein the first angle corresponds to a range of change in the angle at the 25% meridional distance from a shroud tip of the last stage bucket of the turbine.
9. A turbine comprising a diffuser according to claim 1.
10. A turbine according to claim 9, wherein a clearance between a tip of the last stage bucket and an inner casing or shroud is between about 50 to 200 mils.
11. A turbine according to claim 10, wherein the clearance is between about 125 to 160 mils.
12. A method of diffusing exhaust of a turbine, the method comprising:
energizing a boundary layer along a curved exhaust flow guide surface of an exhaust diffuser with over tip leakage of a last stage bucket of the turbine, wherein the curved exhaust flow guide surface is at a first angle with respect to an axis of the turbine and a ratio of a guide surface axial length to the active length of the last stage bucket is between about 0.45 to 0.70.
13. A method according to claim 12, wherein a ratio of a guide surface axial length to the active length is about 0.55.
14. A method according to claim 13, wherein a ratio of an axial length of the exhaust diffuser to the active length is between about 1.35 and 2.0.
15. A method according to claim 12, wherein the curvature of the guide surface comprises a second angle and a third angle, and the first, second and third angles correspond to a range of change in the angle over the previous 25% meridional length of the steam guide at 25%, 50% and 75% meridional distances, respectively.
16. A method according to claim 15, wherein the first angle change is in the range of 0° to 18°, the second angle change is in the range of 14° to 32°, and the third angle change is in the range of 16° to 32°.
17. A method according to claim 15, wherein the second angle is larger than the first angle and the third angle is larger than the second angle.
18. A method according to claim 15, wherein the second angle and the third angle are approximately equal.
19. A method according to claim 15, wherein the first angle corresponds to a range of change in the angle at the 25% meridional distance from a shroud tip of the last stage bucket of the turbine.
20. A method according to claim 12, wherein a clearance between a tip of the last stage bucket and an inner casing or shroud is between about 50 to 200 mils.
US13/419,860 2012-03-14 2012-03-14 Exhaust diffuser for turbine Abandoned US20130243564A1 (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
US13/419,860 US20130243564A1 (en) 2012-03-14 2012-03-14 Exhaust diffuser for turbine
JP2013042473A JP2013189975A (en) 2012-03-14 2013-03-05 Exhaust diffuser for turbine
RU2013111162/06A RU2013111162A (en) 2012-03-14 2013-03-13 TURBINE EXHAUST DIFFUSER, TURBINE AND TURBINE EXHAUST DISTRIBUTION METHOD
EP13158914.5A EP2639404A1 (en) 2012-03-14 2013-03-13 Exhaust diffuser for a turbine
CN2013100811952A CN103306754A (en) 2012-03-14 2013-03-14 Exhaust diffuser for a turbine

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Application Number Priority Date Filing Date Title
US13/419,860 US20130243564A1 (en) 2012-03-14 2012-03-14 Exhaust diffuser for turbine

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US20130243564A1 true US20130243564A1 (en) 2013-09-19

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US (1) US20130243564A1 (en)
EP (1) EP2639404A1 (en)
JP (1) JP2013189975A (en)
CN (1) CN103306754A (en)
RU (1) RU2013111162A (en)

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CN104074554A (en) * 2014-06-13 2014-10-01 东方电气集团东方汽轮机有限公司 Indirect cold cooling last stage moving blade
US20150143810A1 (en) * 2013-11-22 2015-05-28 Anil L. Salunkhe Industrial gas turbine exhaust system diffuser inlet lip
EP3653850A1 (en) 2018-11-16 2020-05-20 Doosan Skoda Power S.r.o. Exhaust diffuser for a steam turbine and corresponding turbine

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EP3054086B1 (en) * 2015-02-05 2017-09-13 General Electric Technology GmbH Steam turbine diffuser configuration
WO2017026904A1 (en) * 2015-08-12 2017-02-16 General Electric Company Diffuser for a turbine engine and method of forming same

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US3552877A (en) * 1968-02-15 1971-01-05 Escher Wyss Ltd Outlet housing for an axial-flow turbomachine
US4013378A (en) * 1976-03-26 1977-03-22 General Electric Company Axial flow turbine exhaust hood
US5257906A (en) * 1992-06-30 1993-11-02 Westinghouse Electric Corp. Exhaust system for a turbomachine
US5494405A (en) * 1995-03-20 1996-02-27 Westinghouse Electric Corporation Method of modifying a steam turbine
US20020018714A1 (en) * 1999-02-15 2002-02-14 Peter Kraus Diffusor without any pulsation of the shock boundary layer, and a method for suppressing the shock boundary layer pulsation in diffusors
US6261055B1 (en) * 1999-08-03 2001-07-17 Jerzy A. Owczarek Exhaust flow diffuser for a steam turbine
US20080063516A1 (en) * 2006-09-08 2008-03-13 Siemens Power Generation, Inc. Adjustable turbine exhaust flow guide and bearing cone assemblies
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US8439633B2 (en) * 2010-01-04 2013-05-14 General Electric Company Hollow steam guide diffuser having increased pressure recovery
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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20150143810A1 (en) * 2013-11-22 2015-05-28 Anil L. Salunkhe Industrial gas turbine exhaust system diffuser inlet lip
US9598981B2 (en) * 2013-11-22 2017-03-21 Siemens Energy, Inc. Industrial gas turbine exhaust system diffuser inlet lip
CN104074554A (en) * 2014-06-13 2014-10-01 东方电气集团东方汽轮机有限公司 Indirect cold cooling last stage moving blade
EP3653850A1 (en) 2018-11-16 2020-05-20 Doosan Skoda Power S.r.o. Exhaust diffuser for a steam turbine and corresponding turbine

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RU2013111162A (en) 2014-09-20
CN103306754A (en) 2013-09-18
EP2639404A1 (en) 2013-09-18
JP2013189975A (en) 2013-09-26

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