EP3023593A1 - Contour d'écoulement pour agencement à un arbre - Google Patents

Contour d'écoulement pour agencement à un arbre Download PDF

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Publication number
EP3023593A1
EP3023593A1 EP14194077.5A EP14194077A EP3023593A1 EP 3023593 A1 EP3023593 A1 EP 3023593A1 EP 14194077 A EP14194077 A EP 14194077A EP 3023593 A1 EP3023593 A1 EP 3023593A1
Authority
EP
European Patent Office
Prior art keywords
inflow
section
cross
flow
channel
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Withdrawn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
EP14194077.5A
Other languages
German (de)
English (en)
Inventor
Simon Hecker
Martin Kuhn
Christoph Kästner
Alexander Todorov
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
Priority to EP14194077.5A priority Critical patent/EP3023593A1/fr
Priority to RU2017121233A priority patent/RU2661915C1/ru
Priority to JP2017527240A priority patent/JP6578360B2/ja
Priority to KR1020177016475A priority patent/KR101902721B1/ko
Priority to EP15794887.8A priority patent/EP3191691B1/fr
Priority to CN201580063065.3A priority patent/CN107075962B/zh
Priority to PCT/EP2015/076312 priority patent/WO2016078984A1/fr
Priority to US15/526,044 priority patent/US10533438B2/en
Publication of EP3023593A1 publication Critical patent/EP3023593A1/fr
Withdrawn legal-status Critical Current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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/026—Scrolls for radial machines or engines
    • 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
    • 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
    • F01D17/18—Final actuators arranged in stator parts varying effective number of nozzles or guide conduits, e.g. sequentially operable valves for steam turbines
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • 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
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/17—Purpose of the control system to control boundary layer

Definitions

  • the invention relates to a turbomachine comprising a rotor rotatably mounted about a rotation axis, a housing arranged around the rotor and a flow channel formed between the rotor and the housing, further comprising an inflow region, which has an inlet connection and opens into an inflow channel, wherein the inflow channel in Substantially has an annular channel cross-section and is fluidly connected to the flow channel, wherein the inflow channel is formed about the axis of rotation, wherein the inflow has an inflow cross section through which a flow medium flows in operation in a flow direction.
  • the invention relates to a method for connecting a Einströmstutzens to a Einströmringkanal.
  • Turbomachines such as steam turbines, essentially comprise a rotor mounted rotatably about a rotation axis, which comprises rotor blades, and a housing formed with guide vanes, wherein a flow channel is formed between the rotor and the housing, which comprises the guide vanes and rotor blades.
  • a thermal energy of the steam is converted into a mechanical energy of the rotor.
  • sub-turbines are known, which are classified for example in high-pressure, medium-pressure and / or low-pressure turbine sections. The division of the sub-turbines into a high-pressure, medium-pressure and low-pressure part is not uniformly defined in the art. In any case, the classification depends on the pressure and the temperature of the incoming and outgoing steam.
  • embodiments are known in which a high-pressure part and a medium-pressure part in a common Outer housing are arranged. Such embodiments require two inflow regions which are arranged close to each other. It is from rotor dynamic aspects required that the high pressure and medium pressure inflow are close to each other, since the axial space is limited. Furthermore, it is less expensive if the high-pressure and medium-pressure inflow regions are arranged close to each other.
  • the invention has set itself the task of specifying an inflow, which leads to improved flow conditions.
  • a turbomachine comprising a rotor rotatably mounted about a rotation axis, a housing disposed around the rotor and a flow channel formed between the rotor and the housing, further comprising an inflow portion having an inflow port and opening into an inflow channel, wherein the Inflow ring channel substantially has an annular channel cross-section and is fluidly connected to the flow channel, wherein the inflow channel is formed about the axis of rotation, wherein the inflow has an inflow cross section through which during operation a flow medium flows in a flow direction, wherein the cross section in the flow direction itself enlarged to a maximum cross-section and then reduced to the annular channel cross-section.
  • the invention thus pursues the approach of changing the flow velocities in the inflow region, which is achieved by a change in geometry of the inflow region.
  • the connection of the cross section between the inflow and the annular channel is modified, the cross-section beyond the annular channel cross-section also increases and after the slowing down of the flow a renewed acceleration, but is achieved in a different direction.
  • the ratio between maximum cross section A2 and inflow cross section A1 is as follows: 1 . 1 ⁇ A 2 / A 1 ⁇ 1 . 7th
  • FIG. 1 shows a cross-sectional view of an inflow region 1 of a turbomachine.
  • the turbomachine may be a steam turbine.
  • the steam turbine is in the FIG. 1 not shown in detail.
  • the steam turbine comprises a rotatably mounted rotor, which is rotatably mounted about a rotation axis 2.
  • a housing for example an inner housing, is arranged around the rotor.
  • a further housing for example an outer housing, can be arranged around the inner housing.
  • a flow channel (not shown) is formed.
  • the rotor comprises several blades on its surface.
  • the inner housing has a plurality of guide vanes on its inner surface.
  • the flow channel is thus formed by the guide and moving blades, wherein in operation, a thermal energy of the steam is converted into a rotational energy of the rotor.
  • the FIG. 1 now shows the inflow region of a steam turbine, wherein the flow channel is directed in the direction of rotation axis.
  • the inflow region 1 comprises an inflow ring channel 3.
  • This inflow is essentially rotationally symmetrical with respect to the rotation axis 2 and has an outer boundary 4.
  • This outer boundary 4 is rotationally symmetrical, at least from the 6 o'clock position 5 to the 3 o'clock position 7.
  • This means that a housing radius 8 is constant from the 6 o'clock position 6 to the 3 o'clock position 7.
  • the inflow region furthermore has an inlet connection 9.
  • the inflow 9 is essentially a tubular connection which connects a steam line, not shown, with the inflow channel 3.
  • the inflow 9 has an individual geometric shape. This form will now be described in more detail.
  • the initial contour 10 forms the connection to a tubular steam line (not shown).
  • the cross section of the initial contour 10 can thus be circular. But there are also other geometric tubular contours possible.
  • This initial contour 10 comprises a lower nozzle limb 11, which is formed such that it adjoins the 6 o'clock position 5. This means that the lower nozzle limiter 11 is directed tangentially to the axis of rotation 2 to the outer boundary 4.
  • the lower nozzle boundary 11 may well be arranged so that in the vicinity of the initial contour 10, this is arranged under the outer boundary 4 at the 6 o'clock position 5.
  • the lower nozzle limiter 11 on the initial contour 10 is thus lower by a vertical distance 12 than the outer boundary 4 in the 6 o'clock position 5.
  • the inflow neck 9 further includes an upper neck boundary 13.
  • the upper neck boundary 13 begins from the initial contour 10 and describes a semicircular arc up to the 3 o'clock position 7. At the 3 o'clock position 7, the upper neck boundary 13 closes tangentially outer boundary 4 on.
  • the inflow pipe 9 thus opens into the inflow ring channel 3.
  • the inflow ring channel 3 essentially has an annular channel cross-section A3 (not shown in detail) and is fluidically connected to the flow channel (not shown). For the sake of clarity is in the FIG. 1 the annular channel cross section A3 in the 9 o'clock position 14, in the 12 o'clock position 15 and in the 3 o'clock position 7 are drawn.
  • the inflow 9 has at the initial contour 10 an inflow cross section A1.
  • the inflow section A1 can have a circular or oval shape.
  • a flow medium in particular steam in a steam turbine as an embodiment of the turbomachine flows in a flow direction 16 in the inflow channel 3.
  • the flow of steam into the inflow channel is complex and will later in the FIG. 6 and FIG. 7 described in more detail.
  • contour is shown for clarity, the flow through a flow line 17.
  • the flow line 17 should be substantially represent the movement of the flow medium in the inflow channel. The flow thus begins at the initial contour 10 and is deflected approximately in the 5 o'clock position 18 in the initial direction.
  • the inflow cross section A1 has a certain value and increases to a maximum cross section A2.
  • the maximum cross section is in the FIG. 1 drawn by a line, where the line also represents a section AA, in FIGS. 3, 4 and 5 will be described in more detail.
  • the cross section in the flow direction 16 is thus reduced to an inflow cross section A1 and then to the annular channel cross section A3. This causes the flow to slow down and accelerate again, but in a different direction.
  • the flow velocity is slowed down in the course of the cross-sectional inlet for entry into the annular channel and then accelerated again, wherein a portion of the velocity in the tangential direction is converted into a velocity component in the radial direction.
  • This radial flow velocity component obstructs the path of the circumferential tangential flow and thus axially forces the vapor into the flow channel. This minimizes inflow losses.
  • FIG. 2 shows a sectional view taken along the line II-II FIG. 1
  • the line 19 shows the inflow section A1 and the lines 20, 21 and 22 three different embodiments, which are described as follows.
  • FIG. 3 shows a section along the line AA FIG. 1
  • the FIG. 6 shows a schematic representation of the flow conditions in the inflow region 1 in a lossy flow.
  • the cutout 23 shows a perspective view of the inflow neck of the inflow region 1.
  • the FIG. 6 shows an embodiment in which the cross section is not increased in the flow direction. In FIG. 6 In addition, it is shown that the flow in the inflow region has a strong peripheral component in a critical region 24.
  • the FIG. 7 On the other hand, an embodiment according to the invention of the inflow neck 9 is shown.
  • the further section 24 shows a perspective view of the inflow neck 9 of the inflow region 1.
  • FIG. 1 shows a single valve arrangement.
  • the contour of a possible second valve guide 25 has been shown.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Control Of Turbines (AREA)
EP14194077.5A 2014-11-20 2014-11-20 Contour d'écoulement pour agencement à un arbre Withdrawn EP3023593A1 (fr)

Priority Applications (8)

Application Number Priority Date Filing Date Title
EP14194077.5A EP3023593A1 (fr) 2014-11-20 2014-11-20 Contour d'écoulement pour agencement à un arbre
RU2017121233A RU2661915C1 (ru) 2014-11-20 2015-11-11 Впускной контур для одновального устройства
JP2017527240A JP6578360B2 (ja) 2014-11-20 2015-11-11 一軸型構造体のための流入輪郭
KR1020177016475A KR101902721B1 (ko) 2014-11-20 2015-11-11 단일 샤프트 배열체를 위한 유입구 윤곽
EP15794887.8A EP3191691B1 (fr) 2014-11-20 2015-11-11 Contour d'écoulement pour agencement à un arbre
CN201580063065.3A CN107075962B (zh) 2014-11-20 2015-11-11 用于单轴装置的入流轮廓部
PCT/EP2015/076312 WO2016078984A1 (fr) 2014-11-20 2015-11-11 Profil d'admission pour dispositif à un seul corps
US15/526,044 US10533438B2 (en) 2014-11-20 2015-11-11 Inflow contour for a single-shaft arrangement

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP14194077.5A EP3023593A1 (fr) 2014-11-20 2014-11-20 Contour d'écoulement pour agencement à un arbre

Publications (1)

Publication Number Publication Date
EP3023593A1 true EP3023593A1 (fr) 2016-05-25

Family

ID=52002686

Family Applications (2)

Application Number Title Priority Date Filing Date
EP14194077.5A Withdrawn EP3023593A1 (fr) 2014-11-20 2014-11-20 Contour d'écoulement pour agencement à un arbre
EP15794887.8A Active EP3191691B1 (fr) 2014-11-20 2015-11-11 Contour d'écoulement pour agencement à un arbre

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP15794887.8A Active EP3191691B1 (fr) 2014-11-20 2015-11-11 Contour d'écoulement pour agencement à un arbre

Country Status (7)

Country Link
US (1) US10533438B2 (fr)
EP (2) EP3023593A1 (fr)
JP (1) JP6578360B2 (fr)
KR (1) KR101902721B1 (fr)
CN (1) CN107075962B (fr)
RU (1) RU2661915C1 (fr)
WO (1) WO2016078984A1 (fr)

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2011104596A2 (fr) * 2010-02-26 2011-09-01 Toyota Jidosha Kabushiki Kaisha Turbocompresseur et passage de roue associé
US20130115076A1 (en) * 2011-11-09 2013-05-09 Richard Bouchard Strut mounting arrangement for gas turbine exhaust case

Family Cites Families (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH579212A5 (fr) * 1974-12-16 1976-08-31 Bbc Brown Boveri & Cie
DE2618194A1 (de) * 1975-04-28 1976-11-11 Garrett Corp Turbomaschine
DE4100777A1 (de) * 1990-12-18 1992-06-25 Asea Brown Boveri Einlassgehaeuse fuer dampfturbine
US5601405A (en) * 1995-08-14 1997-02-11 Coates; George J. Valve apparatus for steam turbines
DE10032454A1 (de) * 2000-07-04 2002-01-17 Man Turbomasch Ag Ghh Borsig Vorrichtung zum Kühlen eines ungleichmäßig stark temperaturbelasteten Bauteiles
US6609881B2 (en) * 2001-11-15 2003-08-26 General Electric Company Steam turbine inlet and methods of retrofitting
EP1624155A1 (fr) 2004-08-02 2006-02-08 Siemens Aktiengesellschaft Turbine à vapeur et procédé d'opération d'une turbine à vapeur
JP2007009820A (ja) 2005-06-30 2007-01-18 Mitsubishi Heavy Ind Ltd タービン車室
US7331754B2 (en) 2005-10-18 2008-02-19 General Electric Company Optimized nozzle box steam path
JP2010209857A (ja) 2009-03-11 2010-09-24 Toshiba Corp 蒸気タービン用ノズルボックスおよび蒸気タービン
JP4869370B2 (ja) 2009-03-13 2012-02-08 株式会社東芝 軸流タービンの蒸気導入部構造体および軸流タービン
ITMI20091740A1 (it) * 2009-10-12 2011-04-13 Alstom Technology Ltd Turbina a vapore assiale alimentata radialmente ad alta temperatura
JP5606299B2 (ja) 2010-12-08 2014-10-15 三菱重工業株式会社 タービンの蒸気入口構造
RU2011153235A (ru) 2011-12-14 2013-06-20 Владимир Николаевич Костюков Турбороторный двигатель
US9683450B2 (en) * 2013-03-13 2017-06-20 General Electric Company Turbine casing inlet assembly construction
RU164736U1 (ru) 2015-02-10 2016-09-10 Александр Евгеньевич Овчаров Силовая роторная турбина

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2011104596A2 (fr) * 2010-02-26 2011-09-01 Toyota Jidosha Kabushiki Kaisha Turbocompresseur et passage de roue associé
US20130115076A1 (en) * 2011-11-09 2013-05-09 Richard Bouchard Strut mounting arrangement for gas turbine exhaust case

Also Published As

Publication number Publication date
KR101902721B1 (ko) 2018-09-28
US10533438B2 (en) 2020-01-14
WO2016078984A1 (fr) 2016-05-26
RU2661915C1 (ru) 2018-07-23
JP2017536499A (ja) 2017-12-07
CN107075962A (zh) 2017-08-18
EP3191691A1 (fr) 2017-07-19
EP3191691B1 (fr) 2018-12-26
CN107075962B (zh) 2019-07-09
JP6578360B2 (ja) 2019-09-18
KR20170083143A (ko) 2017-07-17
US20170314404A1 (en) 2017-11-02

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