EP1611315B1 - Turbomachine - Google Patents

Turbomachine Download PDF

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Publication number
EP1611315B1
EP1611315B1 EP04725711.8A EP04725711A EP1611315B1 EP 1611315 B1 EP1611315 B1 EP 1611315B1 EP 04725711 A EP04725711 A EP 04725711A EP 1611315 B1 EP1611315 B1 EP 1611315B1
Authority
EP
European Patent Office
Prior art keywords
cavity
overflow passage
turbomachine
flow
ejector
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.)
Expired - Lifetime
Application number
EP04725711.8A
Other languages
German (de)
English (en)
Other versions
EP1611315A1 (fr
Inventor
Armin Busekros
Darran Norman
Matthias Rothbrust
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 Technology GmbH
Original Assignee
Alstom Technology 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 Alstom Technology AG filed Critical Alstom Technology AG
Publication of EP1611315A1 publication Critical patent/EP1611315A1/fr
Application granted granted Critical
Publication of EP1611315B1 publication Critical patent/EP1611315B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • 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
    • F05D2260/60—Fluid transfer
    • F05D2260/601—Fluid transfer using an ejector or a jet pump

Definitions

  • the present invention relates to a turbomachine according to the preamble of claim 1. It further relates to a method for operating such a turbomachine.
  • Modern gas turbines are often designed in the high-temperature-loaded part with two-shell enclosures.
  • an annular space is formed between an inner housing and an outer housing, which is often acted upon during operation with cooling air or other coolant.
  • the annular space is formed after stopping the gas turbine without further measures also a vertical temperature stratification, which leads to a delay of the housing.
  • the DE 507 129 as well as the WO 00/11324 suggest to provide means in a bivalve casing of a turbine to disturb the stable temperature stratification by forced flow within the space.
  • it is essentially proposed to convey fluid from one point of the annular space to another point of the annular space outside the annular space, whereby a compensating flow is induced within the annular space.
  • the documents indicate that an overflow channel is preferably to be arranged outside the machine housing, which connects two locations located at different circumferential positions of the housing, and to arrange a circulation fan for driving the equalizing flow within this overflow channel. In practice, the drive of the circulating fan proves to be problematic.
  • a drive shaft of the blower which from a outside of the overflow channel arranged engine to within arranged fan wheel must be reliably sealed under operating conditions. Due to the prevailing high pressures, which can reach values of 30 bar and above in modern gas turbines, and which can be even higher with steam turbines, and the temperatures which can even reach up to 500 ° C in the cooling air, this task is only To solve with great effort, and over a long period of operation is a latent failure risk.
  • a turbo-machine according to the prior art is from the document US 2,650,794 known.
  • the object of the invention is to provide a turbomachine of the type mentioned, which avoids the disadvantages of the prior art.
  • the core of the invention is thus to arrange an ejector within the overflow, through which, if necessary, a propellant flow for driving the flow through the overflow is conductive. It is therefore not necessary to seal a passage of a movable member through the wall of the overflow. Because on the one hand the mass flow of the propellant which is passed through the ejector, is significantly lower than the design mass flow of the overflow, and on the other hand, the flow velocity through the ejector should be high anyway, for the supply to the ejector much smaller flow cross-sections are advantageously used for the overflow , Typically, the design mass flow of the ejector is about 8% to 15%, in particular 10%, of the design mass flow of the overflow channel.
  • the ejector inflow line can be isolated from the volume of the cavity in a much simpler manner by a non-return and / or a shut-off device to let.
  • the Ejektorströmung so essentially serves as a propellant, and an external auxiliary medium can be used, there are great freedoms in the choice of the appropriate drive source.
  • the ejector flow does not necessarily have to be driven by a fan, but it can also be used, for example, air from a compressed air system or steam from a boiler. Because the system is operated in the plant standstill, after the shutdown of the turbomachine, there is essentially ambient pressure during operation of the ejector in the cavity.
  • the propellant source for the ejector is selected so that the pre-pressure of the propellant is 1.3 to 3 times, preferably 1.5 to 2 times, the pressure in the cavity. It is further preferred if the volume of the cavity is circulated through the flow in the overflow line about 4 to 8 times, preferably about 6 times, per minute. In a very particularly preferred embodiment of the invention, the volume of the cavity is circulated once in about 11 seconds. It has been shown that this circulation rate leads to a particularly good homogenization of the temperature distribution in the cavity.
  • the device according to the invention is operated such that when the turbomachine is at a standstill, in particular during a cooling phase of the turbomachine following decommissioning, a fluid is passed as blowing agent through the ejector into the overflow channel, where it drives a flow through which the gas content of the cavity is circulated becomes.
  • the ejector supplies a fluid mass flow to the cavity which, in preferred embodiments of the invention, is in the range of 0.5% to 2% and most preferably around 1% of the contents of the cavity, such that the contents of the cavity are exchanged once in the range of 50 to 200 seconds. This is in contrast to the prior art, not a completely closed system.
  • ambient air or air from an auxiliary air system can be used as propellant.
  • This can be used to advantage in order to support the homogenization of the temperature distribution, and to shorten the cooling phase.
  • fluid is removed at a lower location of the housing cavity and mixed with cold ambient air by the ejector flow, and this mixed overflow is reintroduced in the upper part of the cavity, this adds to an additional, quite desirable, cooling in the upper housing segments. Due to this additional cooling effect due to the externally supplied propellant flow additional cooling is effected, with the appropriate structural design just where it is desired, namely in the tend to be rather hot, upper part.
  • the propellant of the ejector is preheated, while it can be passed over or through other heated components of the turbomachine, for example.
  • medium must flow out of the cavity; This is preferably done by the coolant path of the turbomachine.
  • the cavity is in particular formed between an inner and an outer housing of the turbomachine, for example between a combustion chamber wall and an outer housing of a gas turbine.
  • the cavity is formed with a substantially annular cross section, in particular as a torus, or with a cross section in the form of a ring segment.
  • the overflow channel is advantageously arranged outside the housing of the turbomachine. This ensures superior accessibility and makes it easy to retrofit existing installations.
  • the overflow channel connects two points arranged substantially at diagonally opposite circumferential positions of the cavity.
  • the mouths of the overflow are also with Advantage disposed at different geodetic heights of the cavity, wherein the downstream end of the overflow, to which the ejector drives the flow, is advantageously located at the higher point.
  • the mouths of the overflow are arranged at a geodetically highest and a geodetically furthest down circumferential position of the cavity, the flow in the Matterstömtechnisch from bottom to top, so to speak from the "bottom" of the cavity to their " Roof ", is addressed.
  • relatively cool fluid is conveyed from the lower part of the cavity into the overflow channel, where it is mixed with the propellant of the ejector, which is generally even cooler.
  • the fluid In the place of the outflow into the cavity, in the upper part, the fluid is warmer, and therefore has a lower density.
  • the introduced cooler fluid decreases, thus inducing a balance flow in the cavity.
  • This equalizing flow is self-regulating to a certain extent: the greater the difference in temperature between the upper part and the lower part of the cavity and the turbomachine casing, the greater the difference in density which drives the flow. This means that the more irregular the temperature distribution in the cavity, the stronger the driving forces which induce a compensating flow for temperature uniformity.
  • the overflow line opens with a defined outflow path in the cavity.
  • the outflow section is in particular such that the outflowing medium is oriented at least with a velocity component in the circumferential direction of the cavity.
  • the outflow section which acts as an outlet guide, opens substantially in the circumferential direction, or such that it outflow direction by an angle of less than 30 °, preferably less than 10 °, in the axial direction against the circumference of the cavity is inclined.
  • the discharge path is designed as a nozzle, so that it acts as an ejector, and also drives the fluid within the cavity.
  • the openings of the overflow channel are arranged in a preferred embodiment of the invention at different axial positions.
  • the resulting helical flow through the cavity then causes a homogenization of the temperature distribution in axialer as well as in the circumferential direction.
  • the cavity has openings for the discharge of fluid, through which fluid can flow out of the cavity.
  • the openings are preferably arranged symmetrically on the circumference, for example in the form of an annular gap, annular segment-shaped gaps, or circumferentially distributed holes.
  • the openings are in fluid communication, for example, with the hot gas path of a gas turbine, so that fluid in the cavity, which is displaced by newly introduced fluid, can flow out into the hot gas path.
  • Hot gas path in this context means the entire flow path from entry into the first turbine guide row through to the exhaust gas diffuser.
  • the fluid can be discharged into the hot gas path via the cooling air path and the cooling openings, for example the first turbine guide row.
  • FIG. 1 Therefore, the thermal block of a gas turbine is shown, with only the part located above the machine axis 10 is shown.
  • the machine shown is a gas turbine with so-called sequential combustion, as for example from the EP 620362 is known. Although their operation for the invention without primary importance, this is the sake of completeness explained in outline.
  • a compressor 1 draws in an air mass flow and compresses it to a working pressure. The compressed air flows through a plenum 2 into a first combustion chamber 3. There, a quantity of fuel is introduced and burned in the air. The resulting hot gas is partially relaxed in a first turbine 4, and flows into a second combustion chamber 5, a so-called SEV combustion chamber.
  • the invention is in each case realized in the region of the cavities 2, 7 surrounding the combustion chambers 3, 5.
  • the cross-sectional view in FIG. 2 is highly schematic, and could represent both a section in the region of the first combustion chamber 3 and in the region of the second combustion chamber 5.
  • an annular cavity 2, 7 is formed in each case.
  • the outer housing is provided with a removal point 15 which is connected to a first, upstream end of an overflow line 14.
  • the second, downstream end 16 of the overflow line opens again at a location substantially diagonally opposite the removal trellis 15 in the cavity.
  • a jet pump arrangement 17 with an ejector is arranged in the overflow line. From a per se arbitrary source for a pressurized medium, a propellant mass flow 18 is passed to the ejector and flows there at a relatively high speed, whereby further in the Kochströmtechnisch befindliches fluid is entrained, and thus a flow through the overflow is induced.
  • the mass flow of the entrained fluid is a multiple of the propellant mass flow; typically, the mass flow of the driven flow in a preferred embodiment of the invention is about 10 times the propellant mass flow.
  • the orientation of the flow from an upstream end 15 to a downstream end 16 is predetermined by the orientation of the ejector.
  • the mouth of the upstream end is located at a geodetically lowest point, and the mouth of the downstream end 16 at a geodetically highest point.
  • the coolest fluid in the cavity is sucked into the overflow 14.
  • This is mixed with the propellant mass flow 18, which is often colder again; For example, it may be about a conveyor fan or a compressor 20 brought ambient air.
  • the fluid emerging at the downstream end of the overflow line has a greater density than the fluid at a location located at the top of the cavity in a geodetic manner.
  • a sinking movement begins in the cavity, which further intensifies a compensation flow 19.
  • This intensification is greater, the greater the density differences in the cavity, ie, the more pronounced the temperature stratification is.
  • the system is self-regulating in one way, and the equalizing flow 19 is all the more intense, the more pronounced the temperature stratification is.
  • the fluid in the cavity is circulated once in about 8 to 15 seconds. With the blowing agent mass flow indicated above, the fluid content in the cavity is exchanged once every 80 to 150 seconds for fresh fluid flowing in via the ejector 17.
  • the device according to the invention is advantageously not operated. Lie in the cavity then temperatures in the typical range from about 350 ° C to about 500 ° C, and the pressure is typically 12 bar to over 30 bar. It is therefore an essential advantage of the invention that, in contrast to the prior art in the highly loaded in terms of temperature and pressure part no moving parts are arranged, and sealed no relatively movable parts such as a drive shaft for a circulating fan Need to become.
  • a propellant blower 20 can be arranged at a low pressure in terms of pressure and temperature point, which on the one hand increases the reliability of the overall system and on the other hand reduces effort and costs.
  • the propellant can of course also come from a compressed air system.
  • a check 23 and a shut-off device 24 are arranged to isolate the propellant supply from the high pressures and temperatures during operation of the gas turbine group.
  • the execution according to FIG. 3 differs from the preceding example in that at the downstream end of the overflow 14, a flow guide 21 is arranged, which is presently designed as a nozzle, such that the outflow flow 22 also in the manner of an ejector as a propellant for a circulation flow 19 in the Cavity 2, 7 acts. This can be a directional flow generated in the cavity.
  • FIG. 4 a perspective view of an annular cavity.
  • the inner boundary 12, 13 is shown only schematically as a solid cylinder. Between this inner boundary and an outer shell 11, a cavity 2, 7 is formed.
  • Distributed in the axial direction are three guided through the outer shell 11, not shown in the representation per se ejectors 21 passed, which are schematically indicated by dashed lines.
  • the ejectors are arranged so that the orientation of the blowing direction of the blowing means 22 in the axial direction at an angle ⁇ against that by a dashed line U indicated circumferential direction is inclined.
  • this angle of attack ⁇ can be restricted to values below 30 °, in particular to values smaller than 10 °.
  • a helical flow, not shown, of the cavity arises, which furthermore helps to avoid an optionally adjusting axial temperature gradient. This is further assisted when the downstream end and the upstream end of an overflow line are located at different axial positions.
  • the invention is in no way limited to being used in the outermost cavities 2, 7.
  • the invention can be realized very simply as well for the combustion chambers 3, 5 or and the space formed between the housing elements 12, 13 and the shaft 9.
  • the application of the invention is by no means limited to gas turbines, but that the invention can be used in a variety of other applications.
  • the application of the invention is not limited to an in Fig. 1 It can also be used in gas turbines with only one or more than two combustors used illustrated gas turbine with sequential combustion.
  • the invention can also be realized in steam turbines.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (15)

  1. Turbomachine, présentant au moins une cavité (2, 7) de section transversale annulaire ou en forme de segment annulaire, un canal de débordement (14) étant prévu, lequel relie l'un à l'autre deux endroits de la cavité situés en des positions périphériques différentes, un éjecteur (17) pour l'entraînement d'un écoulement à travers le canal de débordement (14) depuis une extrémité amont (15) jusqu'à une extrémité aval (16) du canal de débordement étant disposé à l'intérieur du canal de débordement,
    caractérisée en ce qu'un dispositif de conduite de sortie (21) est disposé au niveau de l'embouchure aval (16) du canal de débordement (14), à travers lequel le canal de débordement débouche dans la cavité et lequel confère à l'écoulement sortant (22) un sens d'écoulement défini.
  2. Turbomachine selon la revendication 1, caractérisée en ce que le sens d'évacuation de l'écoulement du dispositif de conduite de sortie est orienté essentiellement dans la direction périphérique (U) de la cavité, et/ou est incliné dans la direction axiale avec un angle (α) inférieur à 30°, de préférence inférieur à 10°, vers la direction périphérique de la cavité.
  3. Turbomachine selon la revendication 1 ou 2, caractérisée en ce que le dispositif de conduite de sortie (21) est une buse.
  4. Turbomachine selon l'une quelconque des revendications 1 à 3, caractérisée en ce que le canal de débordement est disposé à l'extérieur du boîtier (11) de la turbomachine.
  5. Turbomachine selon l'une quelconque des revendications précédentes, caractérisée en ce que le canal de débordement débouche dans la cavité au niveau de deux endroits de la cavité essentiellement diagonalement opposés.
  6. Turbomachine selon l'une quelconque des revendications précédentes, caractérisée en ce que le canal de débordement débouche dans la cavité au niveau de deux positions disposées à des hauteurs géodésiques différentes.
  7. Turbomachine selon la revendication 6, caractérisée en ce que le canal de débordement débouche au niveau d'un endroit le plus élevé et d'un endroit le plus profond de la cavité.
  8. Turbomachine selon la revendication 6 ou 7, caractérisée en ce que l'extrémité aval du canal de débordement est disposée au niveau de l'endroit plus élevé.
  9. Turbomachine selon l'une quelconque des revendications précédentes, caractérisée en ce que les embouchures du canal de débordement sont disposées au niveau de positions axiales différentes du canal de débordement.
  10. Turbomachine selon l'une quelconque des revendications précédentes, caractérisée en ce que des ouvertures sont disposées dans la cavité pour l'évacuation de fluide hors de la cavité.
  11. Procédé pour faire fonctionner une turbomachine selon l'une quelconque des revendications précédentes, dans lequel, à l'arrêt de la turbomachine, en particulier dans une phase de refroidissement suivant un arrêt, un fluide afflue à travers l'éjecteur dans le canal de débordement, et entraîne ainsi un écoulement dans le canal de débordement, caractérisé en ce que l'écoulement afflue par le biais d'un dispositif de conduite de sortie (21) hors du canal de débordement (14) dans une cavité (2, 7) de la turbomachine avec un sens d'écoulement défini.
  12. Procédé selon la revendication 11, caractérisé en ce que le débit massique à travers le canal de débordement est dimensionné de telle sorte que le volume de la cavité soit recirculé entre 4 fois et 8 fois, de préférence 6 fois, par minute.
  13. Procédé selon la revendication 11 ou 12, caractérisé en ce que le débit massique à travers l'éjecteur vaut entre 8 % et 15 %, de préférence 10 %, du débit massique à travers le canal de débordement.
  14. Procédé selon l'une quelconque des revendications 11 à 13, caractérisé en ce que du fluide s'écoule de la cavité à travers le chemin de réfrigérant de la turbomachine.
  15. Procédé selon l'une quelconque des revendications 11 à 14, caractérisé en ce que le fluide est chauffé avant l'afflux vers l'éjecteur.
EP04725711.8A 2003-04-07 2004-04-05 Turbomachine Expired - Lifetime EP1611315B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH6282003 2003-04-07
PCT/EP2004/050442 WO2004090291A1 (fr) 2003-04-07 2004-04-05 Turbomachine

Publications (2)

Publication Number Publication Date
EP1611315A1 EP1611315A1 (fr) 2006-01-04
EP1611315B1 true EP1611315B1 (fr) 2015-07-29

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EP04725711.8A Expired - Lifetime EP1611315B1 (fr) 2003-04-07 2004-04-05 Turbomachine

Country Status (4)

Country Link
US (1) US7766610B2 (fr)
EP (1) EP1611315B1 (fr)
CN (1) CN100516469C (fr)
WO (1) WO2004090291A1 (fr)

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US20170002683A1 (en) * 2015-07-02 2017-01-05 General Electric Company Steam turbine shell deflection fault-tolerant control system, computer program product and related methods
US11149642B2 (en) 2015-12-30 2021-10-19 General Electric Company System and method of reducing post-shutdown engine temperatures
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US20170306846A1 (en) * 2016-04-22 2017-10-26 General Electric Company Ventilation system for turbomachine using bladeless airflow amplifier
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US10337405B2 (en) 2016-05-17 2019-07-02 General Electric Company Method and system for bowed rotor start mitigation using rotor cooling
US10583933B2 (en) 2016-10-03 2020-03-10 General Electric Company Method and apparatus for undercowl flow diversion cooling
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EP3907443A1 (fr) * 2020-05-06 2021-11-10 Carrier Corporation Circuit de réfrigération d'éjecteur et procédé de fonctionnement de celui-ci
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CN116346864B (zh) 2023-05-30 2023-08-01 成都秦川物联网科技股份有限公司 基于智慧燃气物联网的超声波计量补偿方法、系统和介质

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Also Published As

Publication number Publication date
CN1802489A (zh) 2006-07-12
WO2004090291A1 (fr) 2004-10-21
US7766610B2 (en) 2010-08-03
EP1611315A1 (fr) 2006-01-04
CN100516469C (zh) 2009-07-22
US20060073010A1 (en) 2006-04-06

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