EP3191691A1 - Profil d'admission pour dispositif à un seul corps - Google Patents

Profil d'admission pour dispositif à un seul corps

Info

Publication number
EP3191691A1
EP3191691A1 EP15794887.8A EP15794887A EP3191691A1 EP 3191691 A1 EP3191691 A1 EP 3191691A1 EP 15794887 A EP15794887 A EP 15794887A EP 3191691 A1 EP3191691 A1 EP 3191691A1
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.)
Granted
Application number
EP15794887.8A
Other languages
German (de)
English (en)
Other versions
EP3191691B1 (fr
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
Publication of EP3191691A1 publication Critical patent/EP3191691A1/fr
Application granted granted Critical
Publication of EP3191691B1 publication Critical patent/EP3191691B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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.
  • Steam turbines essentially comprise a rotor rotatably mounted about an axis of rotation, which comprises rotor blades and a housing formed with vanes, wherein between the rotor and the housing a flow channel is formed, which comprises the guide vanes and rotor blades.
  • a thermal energy of the steam is converted into mechanical energy of the Ro ⁇ tors.
  • 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 are arranged in a common outer housing. Such embodiments require two inlet areas, which are close together angeord ⁇ net. 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 annular channel is formed substantially rotationally symmetrical about the axis of rotation.
  • the velocities of the steam in the annular channel should be as even and as small as possible.
  • the flow conditions in the annular channel are at other than in one-valve arrangements.
  • Einventilan the steam flows through only one inflow into the annular channel.
  • the cross section of the annular channel is usually larger than the cross section of the ring ⁇ channel in a two-valve arrangement. This are first and foremost ⁇ union production so that the flow rates are maintained at egg nem low level.
  • the invention has set itself the task of specifying a single-flow region, which leads to improved flow conditions.
  • a steam turbine 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 inflow and opens into an inflow channel, wherein the Einströmringkanal 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 flows during operation, a flow medium in a flow direction, wherein the cross section in flow ⁇ direction enlarged to a maximum cross section and then reduced to the annular channel cross-section.
  • Figure 1 is a schematic cross-sectional view of a ⁇ ström sess.
  • FIG. 4 shows a section A-A from FIG. 1 in an alternative embodiment
  • Figure 5 is a section A-A of Figure 1 in an alternative embodiment
  • FIG. 1 shows a cross-sectional view of an inflow region 1 of a steam turbine.
  • the steam turbine is not shown in detail in FIG.
  • the steam turbine ⁇ includes 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 out ⁇ forms.
  • the rotor has 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.
  • 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.
  • the inflow region 1 is substantially rotationally symmetrical with respect to the rotation axis 2 and has an outer boundary 4.
  • This outer Begren ⁇ Zung 4 is rotationally symmetrical at least at 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 Stutzenbegrenzung 11 is directed tangentially to the axis of rotation 2 to äu ⁇ ßeren boundary 4.
  • the lower Stutzenbegrenzung 11 is directed tangentially to the axis of rotation 2 to äu ⁇ ßeren boundary 4.
  • the lower Stutzenbegrenzung 11 is directed tangentially to the axis of rotation 2 to äu ⁇ ß
  • Stub 11 may well be arranged so that in the vicinity of the initial contour 10, this is located 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 9 further comprises an upper
  • Nozzle restriction 13 The upper nozzle limiter 13 starts from the initial contour 10 and describes a semicircular arc upwards to the 3 o'clock position 7. At the 3 o'clock position 7, the upper nozzle limiter 13 adjoins tangentially to the outer boundary 4.
  • the Einströmstutzen 9 thus opens into the Einströmringkanal 3.
  • the Einströmringkanal 3 includes an annular channel cross-section A3 (not shown in detail) substantially and is in fluid communication with the flow channel ⁇ (not shown). For the sake of Anschau ⁇ friendliness is in the figure 1, the annular channel cross-section A3 in the 9 o'clock position 14, located at the 12 o'clock position 15 and in the 3 o'clock position. 7
  • the inflow 9 has at the initial contour 10 an inflow cross-section AI.
  • the inflow cross section AI may have a circular or oval shape.
  • a flow medium in particular steam flows through the steam turbine in a flow direction 16 in the
  • Inflow ring channel is complex and will be described later in Figure 6 and Figure 7 in more detail.
  • the Strö ⁇ mung line 17 should essentially the movement of the flow-medium represent in Einströmringkanal.
  • 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 AI has a value and increases to a maximum cross section A2.
  • the maximum cross section is drawn in the figure 1 by a line, the line also has a
  • Section AA represents, which is described in more detail in Figure 3, 4 and 5.
  • the cross section in the flow direction 16 is thus reduced to an inflow cross section AI and then to the annular channel cross section A3.
  • the flow velocity is slowed down in the annular channel in the Ver ⁇ course of the cross-sectional inlet for entry and then accelerated again, a proportion of the speed in the tangential direction is converted into a velocity component in the radial direction.
  • This radial flow velocity component ver ⁇ locks the circumferential tangential flow path, and thus presses the steam axially into the flow channel. This minimizes inflow losses.
  • FIG. 2 shows a sectional view along the line II-II from FIG. 1.
  • the line 19 shows the inflow cross-section AI and the lines 20, 21 and 22 three different embodiments which can be described as follows.
  • FIG. 3 shows a section along the line AA from FIG. 1.
  • FIGS. 4 and 5 show further cross sections along the interface AA from FIG. 1 for different ratios.
  • 6 shows a schematic representation of the Strö ⁇ flow conditions in the inlet 1 at a flow mannbe ⁇ adhered.
  • section 23 is a perspective view of the inflow of Einström Schemes 1 ge ⁇ shows.
  • Figure 6 this shows an embodiment in which the cross section is not increased in the flow direction ⁇ .
  • FIG. 6 shows that the flow in the inflow region has a strong peripheral component in a critical region 24.
  • FIG. 7 shows an embodiment according to the invention of the inflow neck 9.
  • the further section 24 shows a perspective view of the inflow neck 9 of the inflow region 1. It can be seen that at an initial contour 10 the lateral cross section AI in the direction of flow is maximized - Cross section A2 is increased and then reduced to a kon ⁇ constant annular channel cross-section A3.
  • the embodiment shown in Fi gur ⁇ 1 shows a Einventilan extract. For reasons of clarity, the contour of a possible borrowed 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)

Abstract

La présente invention concerne une turbine à vapeur pourvue d'un canal annulaire (3) d'admission qui est relié fluidiquement à une tubulure d'admission (9), ladite tubulure d'admission (9) étant conçue de telle sorte qu'un flux entrant est tout d'abord ralenti, puis accéléré et simultanément dévié.
EP15794887.8A 2014-11-20 2015-11-11 Contour d'écoulement pour agencement à un arbre Active EP3191691B1 (fr)

Applications Claiming Priority (2)

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
PCT/EP2015/076312 WO2016078984A1 (fr) 2014-11-20 2015-11-11 Profil d'admission pour dispositif à un seul corps

Publications (2)

Publication Number Publication Date
EP3191691A1 true EP3191691A1 (fr) 2017-07-19
EP3191691B1 EP3191691B1 (fr) 2018-12-26

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 Before (1)

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

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)

Family Cites Families (18)

* 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
JP2011179370A (ja) * 2010-02-26 2011-09-15 Toyota Motor Corp ターボチャージャおよびそのホイールハウジング
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
US8944753B2 (en) * 2011-11-09 2015-02-03 Pratt & Whitney Canada Corp. Strut mounting arrangement for gas turbine exhaust case
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

Also Published As

Publication number Publication date
JP6578360B2 (ja) 2019-09-18
RU2661915C1 (ru) 2018-07-23
KR101902721B1 (ko) 2018-09-28
US20170314404A1 (en) 2017-11-02
EP3191691B1 (fr) 2018-12-26
US10533438B2 (en) 2020-01-14
CN107075962A (zh) 2017-08-18
EP3023593A1 (fr) 2016-05-25
JP2017536499A (ja) 2017-12-07
WO2016078984A1 (fr) 2016-05-26
CN107075962B (zh) 2019-07-09
KR20170083143A (ko) 2017-07-17

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