EP3006672A1 - Dispositif destiné à influencer l'écoulement dans une turbomachine - Google Patents

Dispositif destiné à influencer l'écoulement dans une turbomachine Download PDF

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Publication number
EP3006672A1
EP3006672A1 EP14188515.2A EP14188515A EP3006672A1 EP 3006672 A1 EP3006672 A1 EP 3006672A1 EP 14188515 A EP14188515 A EP 14188515A EP 3006672 A1 EP3006672 A1 EP 3006672A1
Authority
EP
European Patent Office
Prior art keywords
housing
recesses
gap
blade ring
flow
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Withdrawn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
EP14188515.2A
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German (de)
English (en)
Inventor
Markus Schatz
Damian Prof.Tekn.Dr. Vogt
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.)
Universitaet Stuttgart
Original Assignee
Universitaet 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 Universitaet Stuttgart filed Critical Universitaet Stuttgart
Priority to EP14188515.2A priority Critical patent/EP3006672A1/fr
Priority to PCT/EP2015/073362 priority patent/WO2016055606A1/fr
Priority to EP15778648.4A priority patent/EP3204614B1/fr
Publication of EP3006672A1 publication Critical patent/EP3006672A1/fr
Withdrawn legal-status Critical Current

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    • 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.
  • turbines in the sense of the present patent application includes turbines and compressors.
  • the output 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 the still existing in this area kinetic energy of the flow, such as an air or steam flow, in potential energy in shape from static pressure, which is called pressure recovery.
  • pressure recovery 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 back pressure at the outlet, so that a higher Enthalpiege couple is available, d. H. more work is done and thus the efficiency of the turbine is increased.
  • a maximum pressure recovery in a diffuser is achieved at an opening angle, at which just no flow separation occurs.
  • 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 backflows within the diffuser, which ultimately results in an insufficient delay of the flow. This reduces the pressure recovery and can sometimes even be negative.
  • the described, occurring in the case of flow separation sudström which are usually not stationary, but can trigger significant pressure and speed fluctuations within the diffuser, which can also lead to structural mechanical problems within the diffuser.
  • diffusers are nowadays usually designed very carefully, in that the diffuser is either quite long or has a small opening angle, whereby a lower pressure recovery is accepted.
  • a generic device and a corresponding turbine are from the US 2012/0102956 A1 known.
  • a gap having a width of 90 to 150 mm is provided between the housing and the turbine blades, through which a leakage flow is to be generated in order to energize a boundary layer along an outer wall of a subsequent diffuser.
  • the gap according to the invention having a discontinuous height around the circumference of the blade ring, 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 With constant pressure recovery enabled
  • the solution according to the invention thus allows significantly “more aggressive", d. H. With the same ratio of inlet to outlet area, shorter diffusers can be built so that system costs can be significantly reduced.
  • 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.
  • 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.
  • a structurally very simple to implement embodiment of the device is obtained when the discontinuous height having gap is formed by recesses on the blade ring.
  • the blade ring has a shroud with a circumferential sealing tip, wherein the circumferential sealing tip is interrupted by recesses to form the discontinuous height having gap.
  • the gap having the discontinuous height is formed in that at least one of the blades of the blade ring has a shorter length than another blade of the blade ring.
  • 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.
  • 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.
  • 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 recesses 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 enables a uniform distribution of the regions with an increased gap mass flow and 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 10. From claim 11 results in a turbomachine with a device according to the invention, arranged in a compressor or turbine section.
  • Fig. 1 shows in a very schematic manner a turbomachine 1, which is formed in the present case as a gas turbine and a housing 1a, an inlet opening 2 and an outlet opening 3 has.
  • the turbomachine 1 is flowed through in the direction denoted by "x" by a working fluid, for example a gas, with the aim of driving a shaft 4 mounted in the housing 1a, for example in the case of the use of the turbomachine 1 in FIG to generate electricity for a power plant.
  • a working fluid for example a gas
  • the turbomachine 1 has, in the flow 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 in Fig. 1 are indicated only very schematically, are surrounded by the housing 1a.
  • 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 various embodiments of a device 10 are shown, which serve to influence the flow in the turbomachine 1. All embodiments of the device 1 have in common that between the housing 1a and the blade ring 9 is a around the circumference of the blade ring 9 a discontinuous height exhibiting gap 11 is located.
  • the gap 11 is formed by recesses 12 on the blade ring 9.
  • the blade ring 9 a shroud 13 with a circumferential sealing tip 14 which is interrupted by the recesses 12 to form the gap 11.
  • 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.
  • By the shroud 13, a stiffening of individual blades 15 of the blade ring 9 is reached, of which, for reasons of clarity in the figures, individual have been omitted.
  • the alternating presence of the sealing tip 14 and the recesses 12 in the sealing tip 14 leads to the described discontinuity of the height of the gap 11.
  • FIGS. 3 and 4 This discontinuity of the height of the gap 11 is in the two sections of FIGS. 3 and 4 also very clearly visible. While Fig. 3 shows a section through the area in which the sealing tip 14 is present and the gap 11 between the blade ring 9 and the housing 1a has a small height, shows Fig. 4 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 11 between the blade ring 9 and the housing 1a is much larger than in the Fig. 3 shown area.
  • the recesses 12 each have a size such that the sealing tip 14 is not present in the region of the recesses 12, it would also be possible to perform the recesses 12 so that the Seal tip 14 in the region of the recesses 12 has a lower height than in the areas in which the recesses 12 are not present.
  • the discontinuous height of the gap 11 leads to an increased mass flow in the areas in which the gap 11 has a greater width or height than in the areas in which it has a lower height.
  • an improvement of the energization of the boundary layer flowing along the housing 1a and into the diffuser 7 can be achieved.
  • Fig. 5 is the discontinuous height having gap 11 formed by a shortening of individual 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. 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.
  • Fig. 6 illustrated embodiment of the device 10 of a discontinuous height having gap 11 is formed by a plurality of, 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 11 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 to 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 in the same place.
  • the blade ring 9 in the embodiment of Fig. 6 has the shroud 13 with the sealing tip 14, it is also possible to use a blade ring 9 without the shroud 13.
  • a rotatable ring may be mounted in the housing 1a having recesses with which the above-described discontinuous height of the gap 11 is generated. 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 twisting the ring, however, it is possible in this case to generate the increased mass flows at other locations on the inner circumference of the housing 1a.
  • FIG. 7 illustrated embodiment of the device 10 is also a development of in Fig. 6 illustrated embodiment.
  • the recesses 16 are provided in the housing 1 a, to produce the discontinuous height of the gap 11.
  • rotatable ring 17 is mounted, with which the recesses 16 are at least partially closed.
  • the ring 17 has for this purpose alternately recesses 17a and projections 17b, so that by turning the ring 17 which are located in the housing 1a recesses 16 can be closed.
  • the recesses 16 can be completely opened 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 1a, also 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 11 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 rotatable relative to the housing 1a ring. In this case, two rings rotatable relative to the housing 1a would thus be provided.
  • 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.
  • Such an embodiment of the device 10, which differs from the in Fig. 7 illustrated embodiment only differs in that the shroud 13 is provided is in Fig. 8 shown.
  • the recesses 12 or 16 or 17a are preferably around the circumference of the housing 1a or of the blade ring 9 or of the ring 17 arranged distributed equally with small deviations, so that on the one hand reaches a uniform distribution of the areas with an increased gap mass flow and the circumference of the blade ring 9 and on the other hand, a mutual swinging of the blades 15 can be prevented.
  • the described, discontinuous height gap 11 between the blade ring 9 and the housing 1a 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 projects in the flow direction x immediately before the blade ring Diffuser 7 is located.
  • the device 10 can be used both in axial diffusers and in axial-radial diffusers.
  • Another possibility for using the device 10 is in the compressor section 5 in order to prevent fluttering of the blades 15 of the blade ring 9.
  • the housing 1 a can have a porous material, so that the sealing tip 14 can work into the housing 1 a in the event of a longitudinal expansion without the blade ring 9 being damaged.

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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)
EP14188515.2A 2014-10-10 2014-10-10 Dispositif destiné à influencer l'écoulement dans une turbomachine Withdrawn EP3006672A1 (fr)

Priority Applications (3)

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
PCT/EP2015/073362 WO2016055606A1 (fr) 2014-10-10 2015-10-09 Dispositif influençant l'écoulement dans un turbomoteur
EP15778648.4A EP3204614B1 (fr) 2014-10-10 2015-10-09 Dispositif destiné à influencer l'écoulement dans une turbomachine

Applications Claiming Priority (1)

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

Publications (1)

Publication Number Publication Date
EP3006672A1 true EP3006672A1 (fr) 2016-04-13

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EP14188515.2A Withdrawn EP3006672A1 (fr) 2014-10-10 2014-10-10 Dispositif destiné à influencer l'écoulement dans une turbomachine
EP15778648.4A Active EP3204614B1 (fr) 2014-10-10 2015-10-09 Dispositif destiné à influencer l'écoulement dans une turbomachine

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EP15778648.4A Active EP3204614B1 (fr) 2014-10-10 2015-10-09 Dispositif destiné à influencer l'écoulement dans une turbomachine

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EP (2) EP3006672A1 (fr)
WO (1) WO2016055606A1 (fr)

Citations (8)

* 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
EP0702130A2 (fr) * 1994-09-16 1996-03-20 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Extrémité d'aube avec un revêtement coupant
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
US20120102956A1 (en) 2010-10-27 2012-05-03 General Electric Company Turbine exhaust diffusion system and method
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 (2)

* 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
US20130078084A1 (en) * 2011-09-23 2013-03-28 United Technologies Corporation Airfoil air seal assembly

Patent Citations (8)

* 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
EP0702130A2 (fr) * 1994-09-16 1996-03-20 Mtu Motoren- Und Turbinen-Union MàœNchen Gmbh Extrémité d'aube avec un revêtement coupant
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
US20120102956A1 (en) 2010-10-27 2012-05-03 General Electric Company Turbine exhaust diffusion system and method
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

Non-Patent Citations (3)

* Cited by examiner, † Cited by third party
Title
B. A. REICHERT; B. J. WENDT: "fmproving curved subsonic diffuser performance with vortex generators", AIAA-JOURNAL, vol. 34, no. 1, 1996
M. NISHI; Y. KOUICHI; M. KEISUKE: "Controt of separation in a conical diffuser by vortex generator jets", JSME SERIES B, vol. 41, no. 1, 1998
S. FAROKHI: "A Trade-Off Study of Rotor Tip Clearance Flow in a Turbine/Exhaust Diffuser System", ASME-PAPER NO. 87-CT-214, 1989

Also Published As

Publication number Publication date
EP3204614A1 (fr) 2017-08-16
EP3204614B1 (fr) 2022-01-26
WO2016055606A1 (fr) 2016-04-14

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