WO2016055606A1 - Dispositif influençant l'écoulement dans un turbomoteur - Google Patents

Dispositif influençant l'écoulement dans un turbomoteur Download PDF

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Publication number
WO2016055606A1
WO2016055606A1 PCT/EP2015/073362 EP2015073362W WO2016055606A1 WO 2016055606 A1 WO2016055606 A1 WO 2016055606A1 EP 2015073362 W EP2015073362 W EP 2015073362W WO 2016055606 A1 WO2016055606 A1 WO 2016055606A1
Authority
WO
WIPO (PCT)
Prior art keywords
housing
gap
blade ring
recesses
flow
Prior art date
Application number
PCT/EP2015/073362
Other languages
German (de)
English (en)
Inventor
Markus Schatz
Damian VOGT
Original Assignee
Universität Stuttgart
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 Universität Stuttgart filed Critical Universität Stuttgart
Priority to EP15778648.4A priority Critical patent/EP3204614B1/fr
Publication of WO2016055606A1 publication Critical patent/WO2016055606A1/fr

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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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator

Definitions

  • the invention relates to a device for influencing the flow in a turbomachine, with a housing and with at least one, a plurality of blades having rotating within the housing blade ring. Furthermore, the invention relates to a turbomachine with such a device.
  • turbomachine in the sense of the present patent application includes turbines and compressors. Downstream of turbines often diffusers are used, which have the task of delaying the flow at the outlet of the turbine, in order in this way still existing in this area kinetic energy of the flow, such as an air or steam flow, in potential energy in the form of static pressure, which is called pressure recovery.
  • pressure recovery kinetic energy of the flow
  • the flow cross-section is widened from the inlet of the diffuser in the direction of its exit. Due to this enlargement of the cross section of the diffuser, a delay of the flow is achieved.
  • the diffuser causes a decrease in the backpressure at the outlet, so that a higher enthalpy gradient is available,
  • a maximum pressure recovery in a diffuser is achieved at an opening angle at which just no flow separation occurs.
  • Such a flow separation can be caused by the fact that the boundary layer on the wall of the diffuser loses more and more energy with increasing run length and at the same time a pressure increase occurs due to the delay of the flow, which causes a flow reversal and thus a detachment of the flow from the wall within the boundary layer can.
  • Increasing the opening angle of the turbine increases the risk of flow separation.
  • the occurrence of flow separation leads to large-scale backflow within the diffuser, which ultimately results in an insufficient delay of the flow. This reduces the pressure recovery and can sometimes even be negative.
  • a generic device and a corresponding turbine are known from US 2012/0102956 A1.
  • a gap with a height of about 2.3 to 3.8 mm (90 to 150 mils) is provided, through which a leakage flow is to be generated to a boundary layer along an outer wall of a subsequent ßere To energize diffusers.
  • a gap between the rotating parts of the turbomachines on the one hand, i. the shaft and the blades, and the standing parts on the other hand, i. the housing is necessary to allow the relative movement between the components.
  • it is usually attempted to keep the radial gap, ie the distance between the blade ends and the housing with free-standing blades or the free area between the shroud of the blade ring and the housing, as small as possible ,
  • the radial gap should be at least 1/1000 of the blade rim diameter. It should be noted that the gap is reduced during operation of the turbomachine, for example due to the centrifugal force expansion and the different thermal expansion of the housing and blades. These static strains are also superimposed by a radial movement due to shaft vibrations. If the gap is too small, there is a risk that the rotating components of the turbomachine will rub against the housing. This can lead to permanently higher losses or even the destruction of the turbomachine.
  • the minimum gap height is usually not set over the entire width of the blade tip or the axial shroud length, as it could come in this case to a large-scale tarnishing. Rather, as thin as possible structures are mostly used, which may be damaged in the event of a rubbing, whereby the sealing effect wears off, which, however, usually has no major damage or even a failure of the turbomachine result.
  • a device for free-standing blades is described for example in US 2007/02376237.
  • blade rings with shroud latter is usually occupied by one or more sealing tips or ribs, which thereby form one or more vortex chambers in the axial direction and thus increase the sealing effect.
  • This design is also referred to as a labyrinth seal.
  • these sealing tips and the mating surfaces in the housing are often mounted radially offset, so as to produce a stepped labyrinth.
  • the mating surface in the housing is usually provided with a soft coating, which is removed in the event of tearing.
  • the blade tips of free-standing blades such as in the EP 0 702 130 A2 can be performed with a coatable Abradable coating, while the sealing tips of shroud blades can be provided with a blade-shaped geometry, as set out for example in WO 02/25065 A1.
  • a further possibility is to arrange the seals in the housing in radially yielding segments, as described, for example, in US Pat. No. 5,603,510 A or US Pat
  • this object is achieved by the features mentioned in claim 1.
  • the gap according to the invention which has a discontinuous height on the basis of individual recesses around the circumference of the blade ring and passes through in the axial direction, a local increase in the gap flow is achieved via the blade ring.
  • the energization of the boundary layer on the wall of the diffuser so the introduction of energy in this boundary layer can be improved, which leads to a stabilization of the boundary layer flow and ultimately higher pressure recoveries and a shortening of the diffuser at constant pressure recovery possible.
  • the solution according to the invention thus makes it possible to build significantly "more aggressive”, ie with the same ratio of inlet to outlet surface, shorter diffusers, so that the system costs can be significantly reduced. Furthermore, the formation of large return flow areas in a region downstream of the blade ring can be avoided by the gap according to the invention, which otherwise can cause structural mechanical problems due to low-frequency pulsations.
  • the gap surface of the original design is defined here by the free area between the blade ring and the housing in the continuous gap design. Therefore, this gap surface is sometimes referred to as a free surface between the blade ring and the housing.
  • Another advantage of the solution according to the invention is that due to the relatively large gap in certain sections on the circumference of the blade ring, the problem of manufacturing tolerances and the elongation of the turbine blades and the associated change in size of the gap can be avoided.
  • turbomachinery Another well-known problem with turbomachinery is the flutter of the blades, especially when blade rings are used without shrouds. This blade flutter can occur in blade rings used both in compressors and in turbines.
  • the gap having the discontinuous height has a size such that through the same an increase in the free area between the blade ring and the housing with respect to a design with a continuous gap of 5% - 50 % results.
  • a size of the gap ensures that the effects described above are achieved, since in this way locally, ie in the region of the gap, a very large increase in the gap current is achieved, but the total flow losses are kept within acceptable limits.
  • Particularly advantageous is an increase in the free area between the blade ring and the housing over a design with a continuous gap of 7% - 45%, more preferably 9% - 40%, even more advantageously 1 1% - 35%, even more advantageous 13 - 30% and even more favorably 15 - 25% exposed.
  • a structurally very simple to implement embodiment of the device is obtained when the discontinuous height having gap is formed by at least one recess on the blade ring.
  • the blade ring has a shroud with at least one circumferential sealing tip, which is interrupted by at least one axially continuous recess to form the discontinuous height having gap such that through the same an increase in the free area between the Seal tip and the housing compared to a design with a continuous gap of 5% - 50% results.
  • a solution can be put into practice with very little effort, possibly even cost savings over known solutions are possible.
  • recesses which are such that at the relevant points of the gap current can flow substantially unthrottled through the surface between the housing and the shroud. In this way, a suitable speed ratio of the gap flow to the main mass flow is achieved.
  • the at least one recess has a size such that the increase in the free area per recess is at least 1% of the total free area between the sealing tip and the housing without recesses. These are therefore relatively large recesses, resulting in a sufficiently large gap current to achieve the effect described above.
  • the increase in the free area per recess at least 2%, more preferably at least 3%, more preferably at least 4% and more preferably at least 5%, the entire free area between the sealing tip and the housing without recesses is.
  • the area of the at least one recess can amount to at least 50% of the area of the sealing tip over the length of the recess in the circumferential direction. This also represents a possibility for achieving the high gap current described.
  • the gap having the discontinuous height is formed in that at least one of the free-standing blades of the blade ring has a shorter length than another free-standing blade of the blade ring. Even by such a "shortening" of individual blades, the gap current can locally increase considerably.
  • the free surface or the gap surface is defined as the area between the radially outer ends of the blades and the housing.
  • Another embodiment of the invention which can also be realized with little effort, can be that the gap is formed by recesses on the housing or a component connected to the housing.
  • the housing or connected to the housing member radially outside the blade ring has one or more axially continuous recesses, so that an increase in the free area between the blade ring and the housing compared to a design with a continuous gap of 5% - 50% results.
  • a rotatable ring is mounted in the housing, with which the recesses are at least partially closed.
  • the housing has the recesses, which can then be closed with the rotatable ring, which also has recesses. This makes it possible to achieve a control or regulation of the mass flow flowing through the gap according to the invention.
  • Another embodiment may be that in the housing a rotatable ring is mounted, which has the recesses. With such a solution, a change in the position of the recesses around the circumference of the blade ring is possible to produce in certain areas a larger or smaller mass flow.
  • the housing has two mutually rotatable rings, which each have recesses, wherein at least one of the rings is rotatably mounted on the housing.
  • a further embodiment of the invention may consist in that the gap having the discontinuous height is formed by a plurality of recesses, which are arranged distributed equally around the circumference of the housing or the blade ring with small deviations.
  • an equal spacing of the recesses relative to one another allows a uniform distribution of the regions with an increased gap mass flow around the circumference of the blade ring, which leads to a uniform action of the same in the case of a downstream of the turbomachine.
  • a turbomachine with an inventive device arranged in a region in front of a diffuser is specified in claim 15.
  • Fig. 1 is a very schematic representation of a turbomachine according to the invention
  • FIG. 2 shows a first embodiment of the device according to the invention
  • Fig. 3 is a section along the line III-III of Fig. 2;
  • Fig. 4 is a section along the line IV-IV of Fig. 2;
  • FIG. 6 shows a third embodiment of the device according to the invention.
  • Fig. 8 shows a fifth embodiment of the device according to the invention.
  • turbomachine 1 shows in a very schematic manner a turbomachine 1, which in the present case is designed as a gas turbine and has a housing 1 a, an inlet opening 2 and an outlet opening 3.
  • the turbomachine 1 is traversed in the axial direction designated by "x" by a working fluid, for example a gas, with the aim of driving a shaft 4 mounted in the housing 1 a, for example in the case of the use of the turbomachine 1 to generate electricity in a power plant.
  • a working fluid for example a gas
  • the turbomachine 1 has in succession in the axial direction x of the working fluid a compressor section 5, a turbine section 6, a diffuser 7 adjoining the turbine section 6 and a combustion chamber 8 arranged between the compressor section 5 and the turbine section 6.
  • the compressor section 5, the turbine section 6, the diffuser 7 and the combustion chamber 8, which are indicated only very schematically in Fig. 1, are surrounded by the housing 1 a.
  • the turbomachine 1 is a gas turbine.
  • the term "turbomachine” also includes other embodiments, such as For example, a steam turbine that has no compressor and no combustion chamber.
  • Both the compressor section 5 and the turbine section 6 have a plurality of blade rings 9, which are set in rotation by the gas flowing through and thus drive the shaft 4. Since the basic operation of the turbomachine 1 is known, will not be discussed in detail herein.
  • FIGS. 2 to 8 show various embodiments of a device 10 which serve to influence the flow in the turbomachine 1. All embodiments of the device 10 has in common that between the housing 1 a and the blade ring 9 is a around the circumference of the blade ring 9 a discontinuous height exhibiting, in the axial direction x continuous gap 1 1.
  • the gap 1 can be carried out in different ways, it is in each case designed so that by the same a local increase of the gap current over the blade ring 9 and a stabilization of the flow in the boundary layer to the housing 1 a results.
  • the gap 1 1 has a size such that an enlargement of the free area between the blade ring 9 and the housing 1a relative to a not shown in the figures, for the skilled person, however, very easy to understand Version with a continuous gap of 5% - 50% results.
  • the gap 1 1 is formed by a plurality of recesses 12 on the blade ring 9.
  • the blade ring 9 has a shroud 13 with a circumferential sealing tip 14 which is interrupted by the recesses 12 to form the gap 1 1.
  • the sealing tip 14 may be placed on the shroud 13 or be made in one piece with the same.
  • solutions known from the prior art can be used.
  • the recesses 12 in the sealing tip 14 can be easily made by omitting the sealing tip 14 or by cutting, milling or the like.
  • a plurality of recesses 12 are provided.
  • the size of the same is to be regarded as purely exemplary.
  • the recesses 12 go in the axial direction x completely through the sealing tip 14, wherein the size and the number of recesses 12 is preferably selected so that through the gap 1 1, an increase in the free area between the sealing tip 14 and the housing 1 a opposite a version with a continuous gap of 5% - 50% results.
  • Each individual recess 12 preferably has a size such that the increase in the free area per recess 12 is at least 1%, preferably at least 2%, more preferably at least 3%, even more preferably at least 4% and even more preferably at least 5% of the total free Surface between the sealing tip 14 and the housing 1 a without recesses.
  • each of the recesses 12 extends over the entire height of the sealing tip.
  • the area of the at least one recess 12 is at least 50% of the area of the sealing tip 14 over the length of the recess 12 in the circumferential direction.
  • the lower edge of the respective recess 12 may be embodied in different ways, for example obliquely or bent, but preferably straight.
  • the recesses 12 shown very schematically in FIG. 2 are thus shown larger than indicated in these preferred embodiments. To compensate for this, smaller, ie shorter lengths, could be used in the circumferential direction. send recesses 12, a smaller number of recesses 12 and / or recesses 12 with a lower height, ie a smaller extent in the radial direction, be provided.
  • FIGS. 3 and 4 show a section through the region in which the sealing tip 14 is present and the gap 1 1 between the blade ring 9 and the housing 1 a has a small height
  • Fig. 4 shows a section through a portion of the blade ring 9, in which the sealing tip 14 has one of the recesses 12, so that the gap 1 1 between the blade ring 9 and the housing 1 a is much larger than in the area shown in Fig. 3.
  • the recesses 12 each have a size such that the sealing tip 14 in the region of the recesses 12 is not present, it would, as already mentioned, also possible to perform the recesses 12 so that the sealing tip 14 in the region of Recesses 12 has a lower height than in the areas where the recesses 12 are not present.
  • the discontinuous height of the gap 1 1 leads to an increased mass flow in the areas in which the gap 1 1 has a greater height than in the areas where it has a lower height.
  • an improvement of the energization of the housing 1 a along and flowing into the diffuser 7 boundary layer can be achieved.
  • Fig. 5 of the discontinuous height having gap 1 1 is formed by a shortening of individual free-standing blades 15 of the blade ring 9, whereby the recesses 12 are formed.
  • This variant is useful when the blade ring 9 does not have the shroud 13, ie when the blades 15 are free-standing blades. In principle, it may be sufficient if at least one of the blades 15 of the blade ring 9 has a shorter length than another blade 15 of the blade ring 9. Thus, a number other than the illustrated number of blades 15 can be shortened.
  • At least one and at most half of the free-standing blades 15 have a length which is smaller than the average length of the remaining unbacked blades 15, so that an increase in the free area between the respective blade 15 and the Housing 1 a over a version with a continuous gap, ie in an embodiment in which all blades 15 are the same length, from 5% to 50% results.
  • the free-standing blades 15 are shortened such that the increase in the free area by the shortening per free-standing blade 15 at least 1%, preferably at least 2%, more preferably at least 3%, more preferably at least 4% and even more preferably at least 5% , which is the entire free area between the respective free-standing blade 15 and the housing 1 a without recesses.
  • each spaced-apart recesses 16 on the inner circumference of the housing 1 a. Also in this way results in the areas in which the gap 1 1 due to the recesses 16 has a greater height, a larger mass flow, which does not pass through the blade ring 9, but between the blade ring 9 and the housing 1 a and thus contributes to energizing the boundary layer. In contrast to the embodiments of Fig. 2 and Fig. 5, however, this mass flow is stationary, since the recesses 16 are always located in the same place.
  • a rotatable ring can be mounted in the housing 1 a, which has recesses with which the discontinuous height of the gap 1 1 described above is produced. If this ring is kept stationary, the increased mass flows remain at the same locations around the inner circumference of the housing 1 a. By rotating the ring, however, it is possible in this case to produce the increased mass flows at other locations on the inner circumference of the housing 1 a.
  • the embodiment of the device 10 shown in FIG. 7 is likewise a development of the embodiment shown in FIG.
  • the recesses 16 are provided in the housing 1 a, to produce the discontinuous height of the gap 1 1.
  • a rotatable ring 17 is mounted in the housing 1 a, with which the recesses 16 are at least partially closed.
  • the ring 17 has alternately recesses 17a and projections 17b, so that the recesses 16 located in the housing 1a can be closed by a rotation of the ring 17.
  • the recesses 16 can be fully opened in this way, or if the length of the projections 17b of the ring 17 is at least as large as the length of the recesses 16 in the Housing 1 a, also be completely closed. In such a case, the gap 11 would have the same low height around the entire circumference. By the ring 17, the height of the gap 1 1 in the region of the recesses 16 can only be reduced and not increased.
  • These recesses could be provided in a manner not shown in a second, also with respect to the housing 1 a rotatable ring. In this case, two would be provided with respect to the housing 1 a rotatable rings.
  • the blade ring 9 has no shroud. Nevertheless, it is also possible to use a blade ring 9 with the shroud 13.
  • a blade ring 9 with the shroud 13.
  • the size of the axial x through recesses 16 and 17a have, based on the embodiments described above on a size such that through them an increase in the free area between the blade ring 9 and the housing 1 a over a design with a continuous gap from 5% to 50%.
  • each individual recess 16 or 17a again preferably has a size such that the increase in the free area per recess 16 or 17a is at least 1%, preferably at least 2%, more preferably at least 3%. more preferably at least 4%, and more preferably at least 5%, of the total free area between the respective free-standing blade 15 and the housing 1a without recesses.
  • the recesses 12 and 16 or 17a are distributed around the circumference of the housing 1 a or the blade ring 9 and the ring 17 with slight variations, so that on the one hand a uniform distribution of the areas with an increased gap mass flow and the circumference of Blade rim 9 achieved and on the other hand, a mutual swinging of the blades 15 can be prevented.
  • a discontinuous height having gap 1 1 between the blade ring 9 and the housing 1 a can be used in principle at any point of the turbomachine 1.
  • this gap 11 is preferably used only on that blade ring 9 which is directly in the flow direction x located in front of the diffuser 7.
  • the device 10 can be used both in turbines with downstream axial diffusers and downstream axial-radial diffusers.
  • the housing 1 a may have a porous material, so that the sealing tip 14 in the case of a linear expansion in the housing 1 a can work without causing damage to the blade ring 9.

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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)

Abstract

L'invention concerne un dispositif (10) destiné à influencer l'écoulement dans un turbomoteur (1), qui comporte un boîtier (1a) et au moins un aubage (9) comportant plusieurs aubes (15) et tournant à l'intérieur du boîtier (1a). Entre le boîtier (1a) et l'aubage (9) se trouve une fente (11) continue dans la direction axiale (x) et présentant une hauteur discontinue autour de la circonférence de l'aubage (9). À travers cette fente, se produit une augmentation locale du courant par l'intermédiaire de l'aubage (9) ainsi qu'une stabilisation de l'écoulement dans la couche limite par rapport au boîtier (1a).
PCT/EP2015/073362 2014-10-10 2015-10-09 Dispositif influençant l'écoulement dans un turbomoteur WO2016055606A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP15778648.4A EP3204614B1 (fr) 2014-10-10 2015-10-09 Dispositif destiné à influencer l'écoulement dans une turbomachine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP14188515.2A EP3006672A1 (fr) 2014-10-10 2014-10-10 Dispositif destiné à influencer l'écoulement dans une turbomachine
EP14188515.2 2014-10-10

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Publication Number Publication Date
WO2016055606A1 true WO2016055606A1 (fr) 2016-04-14

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PCT/EP2015/073362 WO2016055606A1 (fr) 2014-10-10 2015-10-09 Dispositif influençant l'écoulement dans un turbomoteur

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Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0256790A2 (fr) * 1986-08-07 1988-02-24 AlliedSignal Inc. Virole pour une turbine pourvue d'une couche en céramique
WO2002025065A1 (fr) * 2000-09-25 2002-03-28 Alstom (Switzerland) Ltd Systeme de garniture d'etancheite
EP1413712A1 (fr) * 2002-10-21 2004-04-28 Siemens Aktiengesellschaft Virole pour une turbine avec joint d'extrémité
US20070237627A1 (en) * 2006-03-31 2007-10-11 Bunker Ronald S Offset blade tip chord sealing system and method for rotary machines
EP2538024A1 (fr) * 2011-06-24 2012-12-26 Alstom Technology Ltd Aube dans une turbomachine
DE102012106175A1 (de) * 2011-07-14 2013-01-17 General Electric Co. Strukturierte schleifend abtragbare Beschichtungen für Oberflächen stationärer Dampfturbinenkomponenten

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4878810A (en) * 1988-05-20 1989-11-07 Westinghouse Electric Corp. Turbine blades having alternating resonant frequencies
DE4432998C1 (de) * 1994-09-16 1996-04-04 Mtu Muenchen Gmbh Anstreifbelag für metallische Triebwerkskomponente und Herstellungsverfahren
US9249687B2 (en) 2010-10-27 2016-02-02 General Electric Company Turbine exhaust diffusion system and method
US20130078084A1 (en) * 2011-09-23 2013-03-28 United Technologies Corporation Airfoil air seal assembly

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0256790A2 (fr) * 1986-08-07 1988-02-24 AlliedSignal Inc. Virole pour une turbine pourvue d'une couche en céramique
WO2002025065A1 (fr) * 2000-09-25 2002-03-28 Alstom (Switzerland) Ltd Systeme de garniture d'etancheite
EP1413712A1 (fr) * 2002-10-21 2004-04-28 Siemens Aktiengesellschaft Virole pour une turbine avec joint d'extrémité
US20070237627A1 (en) * 2006-03-31 2007-10-11 Bunker Ronald S Offset blade tip chord sealing system and method for rotary machines
EP2538024A1 (fr) * 2011-06-24 2012-12-26 Alstom Technology Ltd Aube dans une turbomachine
DE102012106175A1 (de) * 2011-07-14 2013-01-17 General Electric Co. Strukturierte schleifend abtragbare Beschichtungen für Oberflächen stationärer Dampfturbinenkomponenten

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EP3006672A1 (fr) 2016-04-13
EP3204614A1 (fr) 2017-08-16
EP3204614B1 (fr) 2022-01-26

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