WO2014175763A1 - Turbomachine et dispositif d'utilisation de chaleur perdue - Google Patents

Turbomachine et dispositif d'utilisation de chaleur perdue Download PDF

Info

Publication number
WO2014175763A1
WO2014175763A1 PCT/RU2013/000362 RU2013000362W WO2014175763A1 WO 2014175763 A1 WO2014175763 A1 WO 2014175763A1 RU 2013000362 W RU2013000362 W RU 2013000362W WO 2014175763 A1 WO2014175763 A1 WO 2014175763A1
Authority
WO
WIPO (PCT)
Prior art keywords
turbo
machine
ring
flow
outlet duct
Prior art date
Application number
PCT/RU2013/000362
Other languages
English (en)
Inventor
Andrey Leonidovich PAVLEVICH
Anton Gaerovich VALEEV
Original Assignee
Siemens Aktiengesellschaft
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 Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Priority to PCT/RU2013/000362 priority Critical patent/WO2014175763A1/fr
Publication of WO2014175763A1 publication Critical patent/WO2014175763A1/fr

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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/30—Exhaust heads, chambers, or the like
    • 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
    • F05D2210/00—Working fluids
    • F05D2210/40—Flow geometry or direction
    • F05D2210/43—Radial inlet and axial outlet

Definitions

  • the invention relates to a turbo-machine according to the preamble of patent claim 1 as well as a waste heat utilization device.
  • Turbo-machines are well known from the general prior art. Such a turbo-machine can be configured as, for example, a steam turbine. Such a turbo-machine can also be used for a waste heat utilization device, the turbo-machine being an expansion device for expanding a working fluid utilized by the waste heat utilizing device.
  • the waste heat utilization device uses a thermodynamic cycle, for example, in the form of an organic ranking cycle (ORC), the working fluid being a working fluid for said thermodynamic cycle.
  • the working fluid can be an organic fluid.
  • the turbo-machine comprises at least one turbine stage and an outlet duct arranged downstream of the turbine stage.
  • the outlet duct is bounded at least partly by at least one wall of the turbo-machine towards the outside of the turbo-machine.
  • Such an outlet duct can be found, for example, in US 5,462,088 A.
  • the turbo-machine also comprises at least one flow element for influencing the flow of the fluid flowing from the turbine stage through the outlet duct.
  • the flow element is arranged in the outlet duct.
  • vanes are used as flow elements for influencing the flow of the fluid, the plates extending throughout the outlet duct in its radial direction. This means that the plates extend perpendicularly to the direction of flow of the fluid.
  • vanes can be, for example, movable in relation to the wall. Alternatively, the vanes cannot be movable in relation to the wall. Adjustable or movable vanes are very complicated with regard to their design and with regard to supporting the movable vanes in the outlet duct. Hence, using adjustable or moveable vanes is very expensive. Vanes which cannot be moved in relation to the wall cannot be adapted to different mass flows of the fluid.
  • vanes which cannot be moved in relation to the wall cannot be used for multimode devices since they can cause local separations of the flow of the fluid. Such separations affect the efficiency of the turbo-machine negatively. It is therefore an object of the present invention to provide a turbo-machine of the previously mentioned kind as well as a waste heat utilization device which can be operated very efficiently and manufactured in a very cost-efficient way.
  • a first aspect of the present invention relates to a turbo-machine, the turbo-machine comprising at least one turbine stage and an outlet duct arranged downstream of the turbine stage, the outlet duct being bounded at least partly by at least one wall of the turbo-machine towards the outside of the turbo-machine.
  • the turbo-machine also comprises at least one flow element for influencing the flow of a fluid flowing from the turbine stage through the outlet duct, the flow element being arranged in the outlet duct.
  • the flow element is configured as a ring having a profile in the form of an airfoil.
  • the ring has a cross-section having an outer contour in the form of an airfoil.
  • the ring is also referred to as ring wing.
  • Said ring or ring wing is closed and extends completely in the circumferential direction of the outlet duct.
  • the ring is not necessarily movable in relation to the wall.
  • the ring is immobile in relation to the wall.
  • the flow field of the fluid can be influenced particularly positively and in a very easy way.
  • the turbo-machine can be operated very efficiently.
  • the costs of the turbo-machine, in particular, for supporting or mounting the ring can be kept to a minimum.
  • the ring can be placed in regions of probable flow separations so that the ring does not affect a core flow of the fluid. Moreover, the ring does not cause additional vortexes if the flow of the fluid is swirled. As a consequence, a multimode device can be operated more efficiently by using the ring comparing with flat plates or vanes as flow elements.
  • the ring in particular, its airfoil is designed in such a way that the ring directs the separated or inclined to be separated flow of the fluid to the wall, thereby reducing or preventing separations and turbulences of the flow of the fluid.
  • the ring is mounted on an inner side of the wall, the inner side bounding the outlet duct.
  • the ring is mounted on the inner side of the wall in such a way that a flow of the fluid between the inner side and the ring is prevented.
  • the fluid cannot flow through a space between the inner side and the ring.
  • the flow of the fluid can be influenced by the ring very efficiently which allows for realizing a particularly efficient operation of the turbo-machine.
  • the ring contacts the inner side of the wall. Thereby, the fluid cannot flow between the inner side and the ring which leads to a very positive flow field of the fluid.
  • additional parts for mounting the ring on the wall can be avoided since the ring is mounted directly on the inner side of the wall.
  • the turbo-machine comprises at least one second ring for influencing the flow of the fluid, the second ring being arranged in the outlet duct, having a profile in the form of an airfoil, and being arranged at a distance from the first ring in the direction of flow of the fluid.
  • the embodiments of the first ring described above can also be regarded as respective embodiments of the second ring and vice versa.
  • the usage of at least two rings allows for realizing a particularly uniform velocity distribution and lower swirling of the flow of the fluid.
  • different combinations of rings which can have different diameters and/or various or different airfoils in order to obtain a desired flow pattern in the outlet duct.
  • the airfoils of the rings differ from each other.
  • the rings in particular, their airfoils can be adapted to different conditions in different areas of the outlet duct thereby influencing the flow of the fluid in a particularly positive way.
  • the first ring has a first diameter and the second ring has a second diameter, the diameters differing from each other.
  • the outlet duct is configured as a diffuser.
  • the first turbine stage has a radial turbine wheel.
  • the fluid flows to an against the radial turbine wheel in its radial direction. Having entered a blade section of the turbine wheel, the fluid flows off the turbine wheel in the axial direction of the turbine wheel into the outlet duct.
  • a second aspect of the invention relates to a waste heat utilization device utilizing a thermodynamic cycle, in particular, an organic rankine cycle, the fluid being a working fluid, in particular, an organic working fluid.
  • the waste heat utilization device comprises at least one turbo-machine according to the first aspect of the invention.
  • Advantageous embodiments of the first aspect of the invention are to be regarded as advantageous embodiments of the second aspect of the invention and vice versa.
  • the turbo-machine is used as an expansion device for the waste heat utilization device, the turbo-machine, in particular, its turbine stage expanding the fluid in the form of the working fluid flowing through the turbo-machine.
  • the turbo-machine can comprise a shaft on which blades are mounted.
  • the turbo- machine can comprise a turbine wheel, in particular, a radial turbine wheel having the blades and being coupled to the shaft.
  • the working fluid flowing through the turbine stage and the turbine wheel drives the shaft about an axis of rotation the shaft is rotatable about.
  • the shaft can be, for example, supported on at least one housing of the turbo-machine by means of a bearing device. By driving the shaft, waste energy in the form of the waste heat contained in the working fluid can be transformed at least partly into mechanical energy provided by the shaft.
  • the turbo-machine can also comprise at least one generator coupled to the shaft.
  • the generator is being capable of transforming the mechanical energy provided by the shaft into electric energy.
  • waste heat contained in the working fluid can be transformed at least partly into electric energy which can be, for example, stored in a battery or guided to an electrical consumer in order to drive said electrical consumer.
  • the waste heat utilization device can be operated particularly efficiently in a very cost-efficient way.
  • a very high amount of waste heat contained in the working fluid can be transformed into mechanical energy or electric energy respectively.
  • FIG 1 a schematic and perspective view of a turbo-machine according to a first embodiment, the turbo-machine comprising exactly one flow element for influencing the flow of a fluid flowing through an outlet duct of the turbo-machine, the flow element being configured as a ring having a profile in the form of an airfoil;
  • FIG 2 a schematic and perspective view of the turbo-machine according to a second embodiment, the turbo-machine comprising two flow elements in the form of rings arranged in the outlet duct;
  • FIG 3 a schematic longitudinal sectional view of the turbo-machine according the first embodiment
  • FIG 4 a schematic longitudinal sectional view of the turbo-machine according to the second embodiment
  • FIG 5 a schematic front view of the turbo-machine according to the first embodiment
  • FIG 6 a schematic front view of the turbo-machine according to the second embodiment.
  • FIG 1 shows a turbo-machine 10 which, for example, can be used for a waste heat utilization device.
  • the waste heat utilization device utilizes a thermodynamic cycle in the form of an organic rankine cycle using a fluid in the form of an organic fluid as a working fluid.
  • the turbo-machine 10 expands the working fluid thereby transforming waste energy in the form of waste heat contained in the working fluid into electric energy.
  • the turbo-machine 10 comprises a diffuser element 12 having at least one wall 14, the diffuser element 12 being illustrated transparently in FIG 1.
  • the diffuser element 12 bounds an outlet duct 16 which is configured as a diffuser since the diameter of the outlet duct 16 gets larger with regard to the direction of flow of the working fluid flowing through the outlet duct 16 downstream of a turbine stage 18 of the turbo- machine 10.
  • the turbo-machine 10 comprises the turbine stage 18 having a turbine wheel 20 which can be seen in FIG 1 since the diffuser element 12 is illustrated transparently.
  • the turbo-machine 10 also comprises a shaft not shown in FIG 1, the turbine wheel 20 being coupled to the shaft.
  • the shaft is rotatably supported on a housing of the turbo- machine 10 about an axis of rotation.
  • the turbine wheel 20 is configured as a radial turbine wheel and has a set of blades 22 via which the turbine wheel 20 and the shaft can be driven about the axis of rotation by the working fluid flowing through the turbine stage 18 and the turbine wheel 20.
  • the working fluid flows against the turbine wheel 20 in its radial direction.
  • the working fluid flows off the turbine wheel 20 in its axial direction.
  • the axial direction of the turbine wheel 20 coincides with the axis of rotation.
  • the outlet duct 16 is arranged downstream of the turbine wheel 20 with regard to the direction of flow of the working fluid through the turbine stage 18. Having flowed through the turbine wheel 20 the working fluid flows off the turbine wheel 20 and into the outlet duct 16, wherein the working fluid is expanded by the turbine stage 18.
  • the turbo-machine 10 can comprise a generator not shown in FIG 1.
  • the generator is coupled to the shaft so that it can be driven by the shaft. Thereby, the waste heat contained in the working fluid can be transformed into electric energy at least partly.
  • the outlet duct 16 is bounded by an inner side 24 of the wall 14 towards the outside 26 of the turbo-machine 10 in the radial direction of the turbine wheel 20 and the outlet duct 16 respectively.
  • the turbo-machine 10 comprises exactly one flow element for influencing the flow of the working fluid flowing from the turbine stage 18 through the outlet duct 16, the flow element being arranged in the outlet duct 16.
  • the flow element is configured as a ring 28 which is also referred to as ring wing since the ring 28 has a profile in the form of an airfoil like a wing of, for example, an aircraft.
  • the ring 28 is mounted on the inner side 24 of the wall 14, wherein the ring 28 contacts the inner side 24. Thereby, the fluid cannot flow between the ring 28 and the inner side 24. In other words, a flow of the fluid between the inner side 24 and the ring 28 is prevented.
  • the ring 28 By means of the ring 28 a very advantageous flow field of the working fluid can be realized.
  • the basic idea behind using the ring 28 is that the flow field in the outlet duct 16 affects the efficiency of the turbo-machine 10 in the form of a turbo generator. The more separation of the flow of the working fluid flowing through the outlet duct 16 occurs the higher the turbulence of the flow is. The higher the turbulence is the lesser the efficiency of the turbo generator is.
  • the outlet of the working fluid can be optimized so that flow separations can be avoided or reduced. This leads to a very high efficiency of the turbo-machine 10.
  • FIG 2 shows the turbo-machine 10 according to a second embodiment.
  • the turbo-machine 10 according to the second embodiment comprises the ring 28 as a first ring and a second ring 30.
  • the second ring 30 is a flow element for influencing the flow of the working fluid flowing through the outlet duct 16, the second ring 30 being arranged in the outlet duct 16.
  • the second ring 30 has a profile in the form of an airfoil like a wing of an aircraft, the second ring 30 being arranged at a distance from the first ring 28 in the direction of flow of the working fluid.
  • the second ring 30 which also contacts the inner side 24 of the wall 14 has a larger diameter than the first ring 28.
  • FIG 3 shows the turbo-machine 10 according to the first embodiment. As can be seen from FIG 3, flow separations in an area 32 inside the outlet duct 16 can be kept to a minimum.
  • FIG 4 an area 32 of the outlet duct 16 of the turbo-machine 10 according to the second embodiment can be seen. Flow separations in the area 32 can be kept to a minimum, too.
  • FIG 5 shows border areas 34 of the outlet duct 16 according to the first embodiment. By means of the ring 28, flow separations especially in the border areas 34 can be kept to a minimum.
  • FIG 6 shows the outlet duct 16 according to the second embodiment.

Landscapes

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

Abstract

L'invention concerne une turbomachine (10) comportant : au moins un étage de turbine (18); une conduite de sortie (16) agencée en aval de l'étage de turbine (18), la conduite de sortie (16) étant renfermée au moins partiellement par au moins une paroi (14) de la turbomachine (10) vers l'extérieur (26) de la turbomachine (10); et au moins un élément d'écoulement (28) destiné à influencer l'écoulement d'un fluide s'écoulant depuis l'étage de turbine (18) au travers de la conduite de sortie (16), l'élément d'écoulement (28) étant agencé dans la conduite de sortie (16), l'élément d'écoulement (28) étant configuré sous la forme d'un anneau (28) ayant un profil sous la forme d'un profil aérodynamique.
PCT/RU2013/000362 2013-04-25 2013-04-25 Turbomachine et dispositif d'utilisation de chaleur perdue WO2014175763A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/RU2013/000362 WO2014175763A1 (fr) 2013-04-25 2013-04-25 Turbomachine et dispositif d'utilisation de chaleur perdue

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/RU2013/000362 WO2014175763A1 (fr) 2013-04-25 2013-04-25 Turbomachine et dispositif d'utilisation de chaleur perdue

Publications (1)

Publication Number Publication Date
WO2014175763A1 true WO2014175763A1 (fr) 2014-10-30

Family

ID=49684054

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/RU2013/000362 WO2014175763A1 (fr) 2013-04-25 2013-04-25 Turbomachine et dispositif d'utilisation de chaleur perdue

Country Status (1)

Country Link
WO (1) WO2014175763A1 (fr)

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0265633A1 (fr) * 1986-09-26 1988-05-04 BBC Brown Boveri AG Turbine axiale
EP0581978A1 (fr) * 1992-08-03 1994-02-09 Asea Brown Boveri Ag Diffuseur à zones multiples pour turbomachine
US5462088A (en) 1992-10-26 1995-10-31 Societe Anonyme Dite: European Gas Turbines Sa Gas turbine exhaust diffuser
US20040091350A1 (en) * 2002-11-13 2004-05-13 Paolo Graziosi Fluidic actuation for improved diffuser performance
DE10255389A1 (de) * 2002-11-28 2004-06-09 Alstom Technology Ltd Niederdruckdampfturbine mit Mehrkanal-Diffusor
WO2007019336A2 (fr) * 2005-08-04 2007-02-15 Rolls-Royce Corporation, Ltd. Diffuseur d'echappement de turbine a gaz
EP1970539A1 (fr) * 2007-03-13 2008-09-17 Siemens Aktiengesellschaft Agencement de diffuseur
US20100064655A1 (en) * 2008-09-16 2010-03-18 General Electric Company System and method for managing turbine exhaust gas temperature
US20120063893A1 (en) * 2010-09-15 2012-03-15 General Electric Company Turbine exhaust plenum

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0265633A1 (fr) * 1986-09-26 1988-05-04 BBC Brown Boveri AG Turbine axiale
EP0581978A1 (fr) * 1992-08-03 1994-02-09 Asea Brown Boveri Ag Diffuseur à zones multiples pour turbomachine
US5462088A (en) 1992-10-26 1995-10-31 Societe Anonyme Dite: European Gas Turbines Sa Gas turbine exhaust diffuser
US20040091350A1 (en) * 2002-11-13 2004-05-13 Paolo Graziosi Fluidic actuation for improved diffuser performance
DE10255389A1 (de) * 2002-11-28 2004-06-09 Alstom Technology Ltd Niederdruckdampfturbine mit Mehrkanal-Diffusor
WO2007019336A2 (fr) * 2005-08-04 2007-02-15 Rolls-Royce Corporation, Ltd. Diffuseur d'echappement de turbine a gaz
EP1970539A1 (fr) * 2007-03-13 2008-09-17 Siemens Aktiengesellschaft Agencement de diffuseur
US20100064655A1 (en) * 2008-09-16 2010-03-18 General Electric Company System and method for managing turbine exhaust gas temperature
US20120063893A1 (en) * 2010-09-15 2012-03-15 General Electric Company Turbine exhaust plenum

Similar Documents

Publication Publication Date Title
RU2631181C2 (ru) Газотурбинный двигатель с радиальным диффузором и укороченной средней частью
US20140314549A1 (en) Flow manipulating arrangement for a turbine exhaust diffuser
EP3088670B1 (fr) Système de refroidissement par film
EP2960460A1 (fr) Turbocompresseur à géométrie variable
WO2014143413A3 (fr) Ensemble joint d'étanchéité comportant des rainures dans un côté orienté radialement vers l'extérieur d'une plateforme dans un moteur à turbine à gaz
EP2871324A2 (fr) Turbine axiale avec une plaque de guidage
CA2775498A1 (fr) Compresseur centrifuge avec rangee d'aubes de stator
JP2017096268A (ja) 可変ピッチファンアクチュエータ
EP2554793B1 (fr) Conduits inter-turbines dotés d'aubes directrices d'un moteur à turbine à gaz
CN104675441A (zh) 包括末端圆角的涡轮翼型件
CN113653566B (zh) 一种燃气涡轮单元体结构
HUE035343T2 (en) Equipment and Procedure for Generating Energy with Server Rankine Cycle
JP2011094616A (ja) タービン翼形部−側壁の一体化
JP2015526691A (ja) 短縮された中間部分を有するガスタービンエンジン
US20130230383A1 (en) Aircraft gas turbine with adjustable fan
EP3170972A1 (fr) Soufflante modulaire pour un moteur à turbine à gaz
CN109209980B (zh) 一种用于轴流压气机的导流板
CA2956912A1 (fr) Profil dynamique destine a une turbine a gaz
JP6192990B2 (ja) 軸流タービン
CN103382855A (zh) 壳动叶轮机构
WO2014175763A1 (fr) Turbomachine et dispositif d'utilisation de chaleur perdue
GB2494873A (en) Axial turbine with inlet and outlet volutes for bi-directional air flow
EP3119991B1 (fr) Turbine radiale centrifuge
JP2018178986A (ja) 可変型ガイドベーンを有する排気ディフューザー、及びこれを含むガスタービン
CN109854376B (zh) 用于燃气涡轮发动机的轴流压缩机和包括所述轴流压缩机的燃气涡轮发动机

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 13799122

Country of ref document: EP

Kind code of ref document: A1

NENP Non-entry into the national phase

Ref country code: DE

122 Ep: pct application non-entry in european phase

Ref document number: 13799122

Country of ref document: EP

Kind code of ref document: A1