US20140212269A1 - Cooling for a fluid flow machine - Google Patents

Cooling for a fluid flow machine Download PDF

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Publication number
US20140212269A1
US20140212269A1 US14/239,139 US201214239139A US2014212269A1 US 20140212269 A1 US20140212269 A1 US 20140212269A1 US 201214239139 A US201214239139 A US 201214239139A US 2014212269 A1 US2014212269 A1 US 2014212269A1
Authority
US
United States
Prior art keywords
piston
equalizing line
equalizing
cooling ribs
turbomachine
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
US14/239,139
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English (en)
Inventor
Christoph Kastner
Rudolf Potter
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.)
Siemens AG
Original Assignee
Siemens AG
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 Siemens AG filed Critical Siemens AG
Assigned to SIEMENS AKTIENGESELLSCHAFT reassignment SIEMENS AKTIENGESELLSCHAFT ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: KASTNER, CHRISTOPH, POTTER, RUDOLF
Publication of US20140212269A1 publication Critical patent/US20140212269A1/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
    • F01D3/00—Machines or engines with axial-thrust balancing effected by working-fluid
    • F01D3/04—Machines or engines with axial-thrust balancing effected by working-fluid axial thrust being compensated by thrust-balancing dummy piston 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
    • F01D3/00—Machines or engines with axial-thrust balancing effected by working-fluid
    • F01D3/02—Machines or engines with axial-thrust balancing effected by working-fluid characterised by having one fluid flow in one axial direction and another fluid flow in the opposite direction
    • 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
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/26—Double casings; Measures against temperature strain in casings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel
    • F02C7/141—Cooling of plants of fluids in the plant, e.g. lubricant or fuel of working fluid
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/31—Application in turbines in steam turbines
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/213—Heat transfer, e.g. cooling by the provision of a heat exchanger within the cooling circuit
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
    • F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/232—Heat transfer, e.g. cooling characterized by the cooling medium
    • F05D2260/2322—Heat transfer, e.g. cooling characterized by the cooling medium steam

Definitions

  • the invention relates to a turbomachine comprising a rotor mounted rotatably about an axis of rotation, an inner housing arranged about the rotor and an outer housing arranged about the inner housing, wherein a first flow region and a second flow region, formed in the opposite flow direction to the first flow region, are arranged between the rotor and the inner housing, wherein the rotor has a thrust-equalizing piston, wherein a piston-equalizing line is formed for introducing steam between the inner housing and the thrust-equalizing piston.
  • turbomachines such as steam turbines
  • hot fresh steam with comparatively high thermal energy is converted into rotational energy of a rotor. This occurs in a flow duct formed by guide vanes and rotor blades.
  • Modern steam turbines have steam temperatures of over 600° C. Such high temperatures place increased demands on the materials to be used.
  • a steam turbine comprises, substantially, a rotatably mounted rotor, an inner housing arranged about the rotor and an outer housing arranged about the inner housing. The temperature distribution over these three components is very different.
  • the fresh steam inflow region is subject to particularly high thermal loading, whereas those regions in which the thermal energy of the steam has already been largely converted into rotational energy, and thus the temperature has dropped, are subject to less loading.
  • Embodiments of steam turbines which have only one flow duct between the rotor and the inner housing are known. Such steam turbines are usually referred to as single-flow steam turbines.
  • Embodiments of steam turbines which have two flow ducts in one outer housing are known. As a rule, such steam turbines are embodied with one inner housing.
  • the flow directions of the flow ducts can in that case be made to be in opposite directions (reverse flow) or in the same direction (straight flow).
  • a turbomachine comprising a rotor mounted rotatably about an axis of rotation, an inner housing arranged about the rotor and an outer housing arranged about the inner housing, wherein a first flow region and a second flow region, formed in the opposite flow direction to the first flow region, are arranged between the rotor and the inner housing, wherein the rotor has a thrust-equalizing piston, wherein a piston-equalizing line is formed for introducing steam between the inner housing and the thrust-equalizing piston, wherein the piston-equalizing line outer surface is embodied enlarged with respect to a pipe outer surface and/or the piston-equalizing line inner surface is embodied enlarged with respect to a pipe inner surface.
  • a substantial consideration of the invention is thus to extract energy from the hot steam which issues from the second flow duct and is guided via the piston-equalizing line.
  • the piston-equalizing line inner surface of the piston-equalizing line is embodied such that it is enlarged with respect to a conventional pipe inner surface which is embodied smooth, as is known.
  • this enlarged surface area improved thermal interaction between the steam in the piston-equalizing line and the piston-equalizing line occurs here, too.
  • outer cooling ribs are arranged on the piston-equalizing line outer surface.
  • the outer cooling ribs are arranged in series in the direction of the piston-equalizing line. It is also the case here that the more outer cooling ribs there are, the better the thermal interaction.
  • the outer cooling ribs are formed as annular disks extending in the radial direction with respect to the direction of the piston-equalizing line. Annular disks are characterized by two surfaces arranged parallel to each other and are thus simple to produce. In an advantageous development, the annular disks are arranged at regular intervals.
  • inner cooling ribs are arranged on the piston-equalizing line inner surface. These inner cooling ribs are arranged in series in the inner circumferential direction and are embodied in such a manner that they do not markedly influence the flow properties of the steam flowing in the piston-equalizing line. For this reason, these inner cooling ribs are embodied as plates, projections or disks in the longitudinal direction or twisted about the longitudinal direction, arranged at regular intervals in an inner circumferential direction. In this case, too, it is important to consider that the greater the surface area achieved by means of the inner cooling ribs, the better the thermal equalization between the steam flowing in the piston-equalizing line and the piston-equalizing line itself.
  • FIG. 1 shows the cross-sectional view of a steam turbine
  • FIG. 2 shows a perspective view of a piston-equalizing line.
  • FIG. 1 shows a steam turbine 1 as an embodiment of a turbomachine.
  • the steam turbine 1 comprises, substantially, a rotor 2 rotatably mounted about an axis of rotation 3 .
  • An inner housing 4 is arranged about the rotor 2 , with a first flow duct 5 , which can also be designated as the high-pressure flow region, being formed between the inner housing 4 and the rotor 2 .
  • the flow direction of the first flow duct 5 is to the left as shown in the representation according to FIG. 1 .
  • steam flows, via a HP fresh steam region 6 , through the inner housing 4 into the first flow duct 5 .
  • the steam flowing into the first flow duct 5 via the high-pressure fresh steam region 6 cools down in the flow direction, emerges from the steam turbine 1 via a HP outflow region 7 and, after an intermediate superheater stage, is reintroduced, via an IP inflow region 8 into the steam turbine, to a second flow duct 9 . Finally, the steam flows out of the steam turbine 1 via the intermediate-pressure outflow region 10 .
  • An outer housing 11 is arranged about the inner housing 4 .
  • the rotor 2 is formed with a thrust-equalizing piston 12 at the end of the first flow duct 5 .
  • a fluidic connection is established, via a piston-equalizing line 13 , between the IP inflow region 8 and the region of the thrust-equalizing piston 12 .
  • This steam issuing from the second inflow region 8 is comparatively hot steam and is guided between the thrust-equalizing piston 12 and the inner housing 4 .
  • some of this comparatively hot steam flows between the thrust-equalizing piston 12 and the inner housing 4 and flows against the outer housing 11 at that point.
  • the outer housing 11 is thus subject to a particularly high thermal load at that point.
  • the piston-equalizing line 13 is therefore formed, according to the invention, as shown in FIG. 2 .
  • the piston-equalizing line 13 is embodied such that the piston-equalizing line outer surface 14 is embodied enlarged with respect to a pipe outer surface.
  • a pipe outer surface 15 is formed with outer cooling ribs 16 (in FIG. 2 , only the first outer cooling rib is provided with a reference sign).
  • the outer cooling ribs 16 are in this case embodied as annular disks which extend in a radial direction 17 .
  • the radial direction 17 is in this context substantially perpendicular to the direction 18 of the piston-equalizing line.
  • outer cooling ribs 16 are in this context arranged in series in the direction 18 of the piston-equalizing line. Particularly advantageously, outer cooling ribs 16 are arranged at regular intervals in the direction of the piston-equalizing line. In this context, the outer cooling ribs 16 are embodied such that the largest possible surface area results on the piston-equalizing line outer surface 19 .
  • the piston-equalizing line inner surface 20 is embodied enlarged with respect to a pipe inner surface 21 .
  • the piston-equalizing line inner surface is formed with inner cooling ribs 22 which are embodied at regular intervals in an inner circumferential direction.
  • the inner cooling ribs 22 are formed as projections extending in a radial direction 17 , which are embodied, so to speak, as disks or longitudinal ribs or as ribs which are twisted about the flow direction 18 .
  • only one cooling rib 22 is provided with a reference sign.
  • the inner cooling ribs 22 thus extend in the direction 18 of the piston-equalizing line and thus establish good thermal contact between the steam in the piston-equalizing line 13 and the piston-equalizing line 13 itself.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US14/239,139 2011-08-30 2012-08-02 Cooling for a fluid flow machine Abandoned US20140212269A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP11179311.3 2011-08-30
EP11179311A EP2565419A1 (de) 2011-08-30 2011-08-30 Kühlung für eine Strömungsmaschine
PCT/EP2012/065103 WO2013029911A1 (de) 2011-08-30 2012-08-02 Kühlung für eine strömungsmaschine

Publications (1)

Publication Number Publication Date
US20140212269A1 true US20140212269A1 (en) 2014-07-31

Family

ID=46651483

Family Applications (1)

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US14/239,139 Abandoned US20140212269A1 (en) 2011-08-30 2012-08-02 Cooling for a fluid flow machine

Country Status (5)

Country Link
US (1) US20140212269A1 (zh)
EP (2) EP2565419A1 (zh)
JP (1) JP2014527597A (zh)
CN (1) CN103782011A (zh)
WO (1) WO2013029911A1 (zh)

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US9380466B2 (en) 2013-02-07 2016-06-28 Commscope Technologies Llc Radio access networks
US9414399B2 (en) 2013-02-07 2016-08-09 Commscope Technologies Llc Radio access networks
WO2018036697A1 (de) * 2016-08-23 2018-03-01 Siemens Aktiengesellschaft Ausströmgehäuse einer dampfturbine
US9936470B2 (en) 2013-02-07 2018-04-03 Commscope Technologies Llc Radio access networks
US10057916B2 (en) 2014-06-09 2018-08-21 Commscope Technologies Llc Radio access networks in which mobile devices in the same communication cell can be scheduled to use the same airlink resource
US10785791B1 (en) 2015-12-07 2020-09-22 Commscope Technologies Llc Controlling data transmission in radio access networks
US10798667B2 (en) 2018-06-08 2020-10-06 Commscope Technologies Llc Automatic transmit power control for radio points of a centralized radio access network that primarily provide wireless service to users located in an event area of a venue
CN113685236A (zh) * 2021-08-23 2021-11-23 华能铜川照金煤电有限公司 一种用于单缸、单列复速级背压汽轮机的平衡活塞装置
US11304213B2 (en) 2018-05-16 2022-04-12 Commscope Technologies Llc Dynamic uplink reuse in a C-RAN
US11395259B2 (en) 2018-05-16 2022-07-19 Commscope Technologies Llc Downlink multicast for efficient front-haul utilization in a C-RAN
US11627497B2 (en) 2018-09-04 2023-04-11 Commscope Technologies Llc Front-haul rate reduction for use in a centralized radio access network
US11678358B2 (en) 2017-10-03 2023-06-13 Commscope Technologies Llc Dynamic downlink reuse in a C-RAN

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DE102013226742A1 (de) 2013-12-19 2015-06-25 Mahle International Gmbh Strömungsmaschine
EP2937510A1 (en) * 2014-04-25 2015-10-28 Siemens Aktiengesellschaft Turbine with improved cooling means
US20180328285A1 (en) * 2017-05-11 2018-11-15 Unison Industries, Llc Heat exchanger

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US911616A (en) * 1908-06-11 1909-02-09 Carl Roth Turbine.
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US1347591A (en) * 1915-05-13 1920-07-27 Roder Karl Compensating axial thrust in multistage turbines
US1499056A (en) * 1922-07-05 1924-06-24 Hollander Aladar Centrifugal pump
US1554230A (en) * 1925-01-06 1925-09-22 Pochobradsky Bedrich Frantisek Steam turbine
US1912785A (en) * 1931-04-03 1933-06-06 Roy I Mills Absorption fin
US2445471A (en) * 1944-05-09 1948-07-20 Salem Engineering Company Heat exchanger
US2717182A (en) * 1945-06-11 1955-09-06 Daniel And Florence Guggenheim Shaft-positioning mechanism for turbine-driven pumps
US2682157A (en) * 1950-11-03 1954-06-29 Heat X Changer Co Inc Gas separation
US2656677A (en) * 1951-07-13 1953-10-27 Adolphe C Peterson Combustion gas and steam power generating unit
US2692763A (en) * 1952-03-08 1954-10-26 Air Preheater Supporting spacer for annular corrugated fins
US3071076A (en) * 1959-04-28 1963-01-01 Tiraspolsky Wladimir Axial pumps
US3754836A (en) * 1972-03-28 1973-08-28 Reyrolle Parsons Ltd Steam turbines
US3828851A (en) * 1972-06-20 1974-08-13 K Takayasu Heat exchanger
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Cited By (28)

* Cited by examiner, † Cited by third party
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US11445455B2 (en) 2013-02-07 2022-09-13 Commscope Technologies Llc Radio access networks
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US10292175B2 (en) 2013-02-07 2019-05-14 Commscope Technologies Llc Radio access networks
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JP2019528398A (ja) * 2016-08-23 2019-10-10 シーメンス アクティエンゲゼルシャフト 蒸気タービンの流出ハウジング
WO2018036697A1 (de) * 2016-08-23 2018-03-01 Siemens Aktiengesellschaft Ausströmgehäuse einer dampfturbine
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CN113685236A (zh) * 2021-08-23 2021-11-23 华能铜川照金煤电有限公司 一种用于单缸、单列复速级背压汽轮机的平衡活塞装置

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CN103782011A (zh) 2014-05-07
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JP2014527597A (ja) 2014-10-16
EP2565419A1 (de) 2013-03-06

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