EP3094953A1 - Turbomachine comportant une conduite de transfert de chaleur - Google Patents

Turbomachine comportant une conduite de transfert de chaleur

Info

Publication number
EP3094953A1
EP3094953A1 EP15702666.7A EP15702666A EP3094953A1 EP 3094953 A1 EP3094953 A1 EP 3094953A1 EP 15702666 A EP15702666 A EP 15702666A EP 3094953 A1 EP3094953 A1 EP 3094953A1
Authority
EP
European Patent Office
Prior art keywords
heat transfer
turbomachine
transfer line
fluid
temperature sensors
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Withdrawn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
EP15702666.7A
Other languages
German (de)
English (en)
Inventor
Dennis Bensing
José Ángel CARVAJAL SOTO
Bernhard Fischer
Pascal Hoffmann
Michael Opheys
Alexander Rambach
Changsheng Xu
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 EP3094953A1 publication Critical patent/EP3094953A1/fr
Withdrawn legal-status Critical Current

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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/02—Arrangement of sensing elements
    • F01D17/08—Arrangement of sensing elements responsive to condition of working-fluid, e.g. pressure
    • 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
    • F02C7/28—Arrangement of seals
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
    • G01K1/00—Details of thermometers not specially adapted for particular types of thermometer
    • G01K1/02—Means for indicating or recording specially adapted for thermometers
    • G01K1/026—Means for indicating or recording specially adapted for thermometers arrangements for monitoring a plurality of temperatures, e.g. by multiplexing
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M15/00—Testing of engines
    • G01M15/14—Testing gas-turbine engines or jet-propulsion engines
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M3/00—Investigating fluid-tightness of structures
    • G01M3/002—Investigating fluid-tightness of structures by using thermal means
    • 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
    • F05D2260/602—Drainage
    • F05D2260/6022—Drainage of leakage having past a seal
    • 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
    • F05D2260/80—Diagnostics

Definitions

  • the present invention relates to a turbomachine having a number of externally accessible component slots, from which leakage gas can escape, wherein the outlet of this leakage gas can be detected by sensors. Furthermore, the present invention relates to a method for operating such a turbomachine.
  • leakage gases can escape unintentionally.
  • Typical locations for the escape of leakage gases are component slots which are accessible ⁇ especially from the outside, however, have a fluid connection to the interior flow space if a leak is present. It may happen, for example. That leakage gases escape from the interior of the machine through such component Strömungsma ⁇ slots to the outside where they can cause damage to the fluid machine or to other functional components attached thereto. For example, exiting from a gas turbine hot gases damage the mounted on the outer surface of the housing fuel hoses, sensors or electronics and other temperature-sensitive components.
  • the objects underlying the invention are achieved by a turbomachine with a number of externally accessible component slots, wherein at least a portion of a component slot is provided with such a heat transfer line ⁇ that at leakage of leakage ⁇ gas from the portion of the component slot this with the heat transfer line thermally interacts, the Heat transfer line is provided with a number of temperature sensors at mutually different locations of the heat transfer line, which temperature sensors are adapted to detect temperature values at the heat transfer line at the different locations.
  • the objects underlying the invention are achieved by a method for operating a turbomachine described in advance as well as below, wherein individual temperature values are simultaneously determined by means of the number of temperature sensors at the different locations of the heat transfer line.
  • part slots are intended to encompass all those part areas in which there are at least two materially separated components.
  • component slots are formed on housing flanges, component joints or generally at those locations where two components are in mechanical contact with each other.
  • the component slots according to the invention an external accessibility he ⁇ possible to.
  • Components of a turbomachine are then externally accessible, if not a removal of components on the housing of the turbomachine is required, after which, for example, only an internal flow space of the turbomachine would be accessible.
  • the external accessibility he ⁇ therefore does not require an opening or removal of
  • housing components to access the component slots in question possibly the removal of surrounding the flow machine insulation can be erforder ⁇ Lich.
  • all accessible to the housing outer wall of the turbomachine components are externally accessible.
  • the number of externally accessible component slots or the number of temperature Sensors may be one or more at different locations of the heat transfer line.
  • At least one exhaust section of a component slot of the flow machine with egg ⁇ ner heat transfer conduit is provided, so that when discharge of leakage gas from the turbomachine via the Ab ⁇ section of the component slit is typically very hot during operation of the turbomachine leakage gas with Heat transfer line can interact thermally. The interaction takes place here in the region of the exit of the
  • the heat transfer line is designed as a fluid line, in which a fluid is guided. If suitable fluids are selected, which can be embodied, for example, as cooling liquids, good heat transfer and thus heat propagation of the heat transferred to the heat transfer line can be ensured. Furthermore, the fluid guided in the fluid line can be fluidly removed from the affected area of the section of the component slot, so that a sensory detection of heat transfer is not required exclusively in the area of the component slot.
  • the heat propagation in the fluid line model and program technology can be easily replicated, so that from the heat profile within the fluid line targeted to the outlet or the outlet amount of leakage gas can be closed.
  • the knowledge of the thermal properties of the fluid and its flow rate is required.
  • the fluid line is designed as a closed fluid line, in which the fluid is moved during operation of the turbomachine by means of a flow generator.
  • a flow generator is, for example, designed as a pump, which allows to guide the fluid in the fluid line at a constant flow rate. From the known Strö ⁇ flow velocity and the heat transfer property of the fluid, as well as from the sensed temperature values so the exit location or exit the amount of leakage gas can be determined.
  • the fluid line is in thermal interaction with a heat exchanger which is adapted to cool the fluid in the fluid line.
  • a heat exchanger which is adapted to cool the fluid in the fluid line.
  • the heat transfer line mit- Is at least one spacer spaced from the portion of the component slot and in particular is supported by this spacer.
  • the spacer thus ensures a time-constant spacing of heat transfer line to component slot, resulting in lower measurement errors.
  • the spacer is thermally insulated from the housing of the turbomachine.
  • the spacer is made of poorly heat-conductive material such as ceramic. Due to this thermal insulation, heat influences on the heat transfer line can be further reduced, whereby measurement errors can be reduced.
  • the different locations of the heat transfer line with temperature sensors are uniformly spaced from one another, in particular over the portion of the component slot uniform voneinan ⁇ spaced. Due to the uniform spacing of all sub-sections which are defined by adjacent temperature ⁇ tursensoren can be treated equally with respect to the evaluation of the temperature values. This results in an evaluation-technical simplification, since the moderately spaced apart temperature sensors stocked section or section can be divided into equal length ranges. To evaluate the temperature changes of the individual determined by temperature sensors adjacent sections are in this case typically be true ⁇ , and combined into an overall view. This can, for example, a local temperature gradient along the Heat Transf ⁇ supply line are determined or a change over time of this gradient. In turn, the exit location of leakage gas or the discharge quantity can be determined in turn. Due to the uniform spacing of the temperature sensors, the detection reliability can also be increased, since all component slot areas are provided substantially uniformly with temperature sensors.
  • deflection means are provided on the turbomachine, which lead leakage gas leakage from the portion of the Bauteilschlit ⁇ zes the leakage gas to the heat transfer line.
  • deflection means are designed in particular as baffles or as slot covers. According to the execution, it is thus possible to more selectively guide the leakage gas to the desired heat transfer to the heat transfer line. Furthermore, it is also possible with the help of these deflecting means
  • the temporal heat input is determined in the heat transfer line at two adjacently arranged locations with temperature sensors.
  • the temporal heat input is determined, for example, in units of kJ / s. Preferably, this determination is made for all sectionab ⁇ sections of the portion of the component slot, which are by ⁇ each two adjacent temperature sensors be ⁇ true. Due to the determination of the heat input not only a heat profile along the heat transfer line can be determined, but also concrete conclusions about the amount of leaking leakage gas can be obtained. This allows to determine a particularly efficient and meaningful technical size to ⁇ rakter accruing better cha.
  • Figure 1 is a side sectional view of components
  • Figure 2 egg a schematic circuit view for determining ei ⁇ nes temperature profile along a section ner heat transfer line according to another embodiment of the flow machine according to the invention;
  • Figure 3 is a side sectional view of components with
  • FIG. 4 shows a plan view of the embodiment of the components of the turbomachine according to the invention shown in FIG.
  • Figure 1 shows a sectional side view through a first embodiment of the flow machine 100 according to the invention, wherein only components 4 of the housing 110 are shown in regions. Typically, this is a housing joint between two housing components.
  • Embodiment ⁇ according to two mutually associated components 4 are provided, which do not allow leakage management in the contact region of both components 4 in trouble-free operation of the turbomachine. In case of failure, however, both components 4 may sometimes be locally spaced so far from each other that leakage gas 3 can escape between the two components 4 to the outside.
  • the outlet direction of the leakage gas 3 is indicated by an arrow, the leakage gas 3 passing through a component slit 1 accessible from the outside.
  • a heat transfer conduit 10 is arranged, which is spaced by schematically shown Abstandhal ⁇ ter 30 of the housing 110th
  • the component ⁇ slot 1 is thus provided with a heat transfer line 10.
  • the spacers 30 are in this case designed such that in case of failure emerging from the component slot
  • the heat transfer line 10 is designed as a metallic wire, which is approximately spaced apart from the section 2 of the component slot 1.
  • FIG. 2 shows a schematic representation of a further embodiment of the turbomachine 100 according to the invention.
  • this embodiment also has a component slot 1 from which leakage gas 3 can emerge in the event of a fault.
  • the component slot 1 is in turn arranged in the region of two components 4 of a housing 110 which are contacted with one another.
  • a heat transfer conduit is attached to a portion 2 of the component 1 slot 10 is arranged ⁇ , which is designed as a fluid line 10, and in which a fluid is passed.
  • the sauceübertragungslei- tung 10 is madebil ⁇ det as a cyclical closed fluid conduit.
  • a flow generator 21 is provided to pressurize the fluid 11 in the heat transfer line 10 with a flow.
  • a flow meter 22 is provided in the heat transfer line 10, which can detect the flow rate of fluid 11 in the fluid line 10.
  • a number of temperature sensors 15 are provided over section 2 of component slot 1, which are arranged at mutually different locations 12 of the heat transfer line with a defined spacing, in particular with the same spacing to the respective neighbor. Occurs now due to a disturbance leakage gas in the region of section 2 of the component slot. 1 out, it comes to a thermal interaction of the
  • the temperature gradient between any two Benach ⁇ disclosed temperature sensors 15 determined, as one local area of the portion 2 are determined, at which are present the highest temperature values, and hence also corresponds to the highest leakage gas outlet.
  • the fluid located in the heat transfer line 10 to 11 is placed ⁇ by means of the flow generator 21 in a uniform flow movement, there is a temporal change of the temperature detected by the temperature sensors 15 raturprofils. Due to this temporal change, knowing the thermal conductivity of the fluid 11 as well as the flow rate of the fluid 11 inference can be Gezo ⁇ gene on the amount of leakage gas escaping.
  • the temporal behavior can be easily emulated by a physical model, for example., From which The required technical ⁇ th values for the exit location as well as the discharge amount of leakage gas can be determined.
  • the heat transfer conduit further comprises a heat exchanger 20 prior which is designed to cool the fluid 11 through thermi ⁇ specific interaction.
  • FIG. 3 shows a side sectional view through a further embodiment of a turbomachine 100 according to the invention in a partial view.
  • approximate shape as already in the execution according to Figure 1 again, only a portion of two contacted with each other components 4 of a housing 110 ge shows ⁇ .
  • the present embodiment has a
  • Housing screw 120 which, in order to avoid tension in the components 4, has appropriate relief slots 5. Clearly these relief slots can be seen in the plan view of Figure 4.
  • two deflection means 40 are arranged in the form of two suitably mounted baffles, which supply the leakage gas specifically to the heat transfer line 10. Consequently, it can be ensured that even in areas with a plurality of interconnected component slots, the leakage gas can be suitably redirected to allow a good detection of the exit ⁇ site as well as leakage amount of leakage gas. Further embodiments emerge from the subclaims.

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Investigating Or Analyzing Materials Using Thermal Means (AREA)

Abstract

L'invention concerne une turbomachine (100) comportant une pluralité de fentes de composant (1) accessibles par l'extérieur, au moins un segment (2) d'une fente de composant (1) étant relié à une conduite de transfert de chaleur (10) de telle manière qu'en cas de sortie de gaz de fuite (3) par le segment (2) de la fente de composant (1), le gaz interagit thermiquement avec la conduite de transfert de chaleur (10), la conduite de transfert de chaleur (10) étant pourvue, en divers emplacements (12), d'une pluralité de capteurs de température (15) conçus pour détecter des valeurs de température sur la conduite de transfert de chaleur (10) au niveau des différents emplacements (12).
EP15702666.7A 2014-02-19 2015-01-21 Turbomachine comportant une conduite de transfert de chaleur Withdrawn EP3094953A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102014203035 2014-02-19
PCT/EP2015/051111 WO2015124361A1 (fr) 2014-02-19 2015-01-21 Turbomachine comportant une conduite de transfert de chaleur

Publications (1)

Publication Number Publication Date
EP3094953A1 true EP3094953A1 (fr) 2016-11-23

Family

ID=52450060

Family Applications (1)

Application Number Title Priority Date Filing Date
EP15702666.7A Withdrawn EP3094953A1 (fr) 2014-02-19 2015-01-21 Turbomachine comportant une conduite de transfert de chaleur

Country Status (3)

Country Link
US (1) US20170009597A1 (fr)
EP (1) EP3094953A1 (fr)
WO (1) WO2015124361A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN108844688B (zh) * 2018-06-25 2023-06-13 华能国际电力股份有限公司 一种用于低温换热器泄漏监测的系统及方法

Family Cites Families (9)

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Publication number Priority date Publication date Assignee Title
US6487860B2 (en) * 2000-12-08 2002-12-03 General Electric Company Turbine engine fuel supply system
US6732982B1 (en) * 2003-04-09 2004-05-11 Bell Helicopter Textron, Inc. Laterally adjustable clamp
US8567450B2 (en) * 2005-01-12 2013-10-29 Smart Pipe Company Lp Methods and systems for in situ manufacture and installation of non-metallic high pressure pipe and pipe liners
US8410946B2 (en) * 2010-03-05 2013-04-02 General Electric Company Thermal measurement system and method for leak detection
US8984856B2 (en) * 2010-04-12 2015-03-24 Hamilton Sundstrand Corporation Flexible fuel system
US20130008180A1 (en) * 2011-07-07 2013-01-10 Diatzikis Evangelos V Method and apparatus for distributed cleft and liberated tile detection achieving full coverage of the turbine combustion chamber
KR20150132124A (ko) * 2013-02-08 2015-11-25 프로브타가렌 에이비 강화된 차등 열식 질량 유량계 어셈블리 및 질량 유량계 어셈블리를 사용하여 질량 유량을 측정하기 위한 방법
FR3021350B1 (fr) * 2014-05-20 2016-07-01 Snecma Procede de detection de fuite de fluide dans une turbomachine et systeme de distribution de fluide
US10273017B2 (en) * 2016-03-15 2019-04-30 The Boeing Company System and method for protecting the structural integrity of an engine strut

Non-Patent Citations (1)

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Also Published As

Publication number Publication date
WO2015124361A1 (fr) 2015-08-27
US20170009597A1 (en) 2017-01-12

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