EP2090786A2 - Structuration de boîtier destinée à la stabilisation de l'écoulement dans une machine de traitement des écoulements - Google Patents

Structuration de boîtier destinée à la stabilisation de l'écoulement dans une machine de traitement des écoulements Download PDF

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Publication number
EP2090786A2
EP2090786A2 EP09150842A EP09150842A EP2090786A2 EP 2090786 A2 EP2090786 A2 EP 2090786A2 EP 09150842 A EP09150842 A EP 09150842A EP 09150842 A EP09150842 A EP 09150842A EP 2090786 A2 EP2090786 A2 EP 2090786A2
Authority
EP
European Patent Office
Prior art keywords
channel
housing
blade
max
compressor
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.)
Granted
Application number
EP09150842A
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German (de)
English (en)
Other versions
EP2090786B1 (fr
EP2090786A3 (fr
Inventor
Carsten Clemen
Henner Schrapp
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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 Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP2090786A2 publication Critical patent/EP2090786A2/fr
Publication of EP2090786A3 publication Critical patent/EP2090786A3/fr
Application granted granted Critical
Publication of EP2090786B1 publication Critical patent/EP2090786B1/fr
Ceased legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0246—Surge control by varying geometry within the pumps, e.g. by adjusting vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
    • F04D29/526—Details of the casing section radially opposing blade tips
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F04D29/685—Inducing localised fluid recirculation in the stator-rotor interface

Definitions

  • the invention relates to a housing with at least one housing structuring for stabilizing the flow in the region of the blade tips of the rotor blades in a turbomachine. Furthermore, the invention relates to a use of the housing in a compressor of a gas turbine. Moreover, the invention relates to a method for stabilizing the flow in the region of the blade tips of the blades in a fluid flow machine by means of the housing.
  • a fluid flow machine especially in a compressor
  • the pressure of a fluid is continuously increased by means of a rotor with blades and a stator with vanes.
  • the stability of the flow of the fluid in the compressor has a significant influence on the efficiency of the compressor and the life of the blades. Therefore, it is an important goal in the design of compressors to reduce flow instabilities, such as those that occur particularly in the blade tip flow around the blades (slit flow), in order to increase the stability limit of the compressor.
  • adjustable guide wheels To actively influence the compressor stability include e.g. adjustable guide wheels.
  • Fig. 1 is a compressor 1 of a jet engine, not shown, with a compressor housing 2, a compressor duct 3, blades 4 and adjustable vanes 5 with adjusting devices 6 according to the prior art shown schematically.
  • the air 7 flows into the compressor and leaves it as compressed air 8.
  • the functioning of the adjustable guide vanes 5 is characterized in that the angle of attack of the moving blades 4 is tracked with a change in the speed of the compressor 1 in order to adjust the flow conditions, that the stability of the housing and profile boundary layers on the rotor blades 4 is maintained.
  • adjustable vanes are very complicated in their construction. There are many items needed, making the compressor heavier and more expensive. In particular, in jet engines, however, an increase in weight through additional facilities is to be avoided. In addition, the adjustment are susceptible to failure. This increases both the maintenance and maintenance costs.
  • Fig. 2 shows a compressor 1 with a channel 10 for returning a partial flow from a rear compressor stage to a front compressor stage, which is known in practice.
  • the compressor 1 of a jet engine essentially comprises a compressor housing 2, a compressor duct 3, blades 4 and vanes 5.
  • the air 7 flows into the compressor and leaves it as compressed air 8.
  • the channel 10 is arranged between the compressor housing 2 and the bypass inner housing 9 of the jet engine. Behind a downstream compressor stage is a tapping point 11, which opens into the channel 10, which leads to a Einblasestelle 12 in front of an upstream compressor stage.
  • Passive influences on compressor stability include casing treatments in the form of small recesses mounted in front of or above the blade tips of the blades on the circumference of the compressor housing and affecting the blade tip flow.
  • the compressor 1 of a jet engine comprises a compressor housing 2, a compressor duct 3, Blades 4 and Vanes 5.
  • the air 7 flows into the compressor and exits it as compressed air 8.
  • At the leading edge 41 of the blade tip 40 of the first blade 4 is a recess 13.
  • the influence of the flow in the area of the blade tip 40 is characterized achieved that the flow at the downstream end of the recess 13 enters the recess 13 and exits at the upstream end of the recess 13 again and thus circulated. This happens because the pressure at the downstream end of the recess 13 is greater than at the upstream end. This pressure difference causes the local recirculation of the flow. As a result, a small amount of energy is transported into the front region of the blade tip 40.
  • the interaction of the flow recirculation with the blade tip overflow leads to a stabilization of the gap flow and thus of the compressor.
  • the recesses are not speed dependent, but can be optimally designed only for one operating point. This means that they are insufficient for stability enhancement under all operating conditions.
  • the invention is therefore based on the object to provide a housing that increases the compressor stability, is simple in construction, has a low weight, works reliably and does not heat the fluid in the fluid flow machine.
  • This object is achieved with a housing having at least one housing structuring for stabilizing the flow in the region of the blade tips of the blades in a fluid power machine according to claim 1. Furthermore, the object is achieved with a method for stabilizing the flow in the region of the blade tips of the rotor blades in a turbomachine according to claim 12.
  • Advantageous embodiments of the invention are contained in the subclaims.
  • the object is achieved in a housing with at least one housing structuring for stabilizing the flow in the area of the blade tips of the rotor blades in a fluid flow machine, wherein the housing structuring is arranged at least in one stage on the inner circumference of the housing.
  • the housing structure is formed as a channel comprising a first end and a second end, wherein the first end opens in the region of the blade tips of a blade ring in the interior of the housing and the second end is closed.
  • Static pressure fields which form on the blades, pull past the channel and cause the air column in the channel to vibrate. At a certain speed, a standing wave is formed in the duct. This creates at the mouth of the channel a pulsating mass flow which stabilizes the flow between the blade tips of the blades and the housing.
  • the arrangement is simple in construction and works reliably.
  • the weight of the compressor is not increased by the channel.
  • the temperature of the flow in the compressor is not increased, as for example in a return of fluid.
  • the channel has a taper at the first end.
  • the rejuvenation enhances the effect of the pulsating mass flow.
  • the length l of the channel at the second end in a range between a minimum length l min and a maximum length l max is speed-dependent adjustable.
  • the housing according to the invention thus combines the advantages of passive housing structures, the be formed by recesses in the housing, (simple design, low weight, no return of hot fluid) with the advantages of active flow control by Verstellleitrate (speed-dependent control).
  • the l length adjustable channel allows future compressors to be designed with higher loaded rotor tips, which can be achieved, for example, by reducing rotor blade counts. This leads to a weight and cost reduction.
  • the channel is rectilinear at least in the range between l min and l max and has a constant cross-section in this region, wherein at the second end of the channel in the longitudinal direction of the channel in the range between l min and l max movable Piston is arranged.
  • the movable piston makes it easy to adjust the length l of the channel.
  • the arrangement of the piston is very easy to implement, requires few parts and has a lower weight than a Verstellleitradsystem according to the prior art.
  • the position of the piston may be controllable by means of an electric, hydraulic or pneumatic drive.
  • an electric drive for example, a stepper motor comes into question. These drives are reliable and can be easily installed in the fluid flow machine.
  • the channel is arranged substantially radially to the inner periphery of the housing.
  • a channel can be easily made, for example, by a core during casting or by subsequent drilling.
  • the channel is arranged at an angle to the longitudinal axis of the housing. Also such a channel can be easily made by a casting core or drilling.
  • the channel is arcuately curved outside the range between l min and l max . This shape allows a length of the channel that exceeds the thickness of the housing wall.
  • the channel is arcuately curved in the region of the first end and in the region between l min and l max parallel to the longitudinal axis of the housing. This arrangement is advantageous when the piston is to move in the axial direction.
  • the position of the first end of the channel is between the trailing edge of the blade and a distance of 1.3 times the axial chord length l ax of the blade at the blade tip as measured from the trailing edge of the blade. This position range is optimal for stabilizing the flow between the blade tips of the blades and the housing.
  • the housing is used in a compressor of a gas turbine.
  • compressor stability is particularly important.
  • the compressor is exposed to high pressures due to pressure and temperature and should not be additionally burdened by flow instabilities.
  • the solution of the problem in a method for stabilizing the flow in the area of the blade tips of the blades in a fluid flow machine by means of the housing, which forms a static pressure field on each blade.
  • the static pressure field travels past the first end of the channel during rotation of the blade and causes the fluid column in the channel to vibrate, creating a standing wave in the channel. which creates a pulsating mass flow at the first end of the channel.
  • This method is based on a simple principle and is very reliable.
  • the method results in that an increase in the compressor pumping limit can be achieved without adversely affecting the compressor efficiency, and that the increase in the pumping limit for the entire speed range of the compressor can be optimally utilized.
  • the standing wave is generated by tuning the natural frequency of the fluid column to the blade follower frequency so that the natural frequency of the fluid column is a multiple of the blade follower frequency of the blades.
  • the tuning of the natural frequency of the fluid column enables an improvement of the stability in all operating areas of the fluid flow machine.
  • the natural frequency of the fluid column can be adjusted as a function of speed by adjusting the length l of the channel.
  • the length l of the channel By adjusting the length l of the channel, a simple adjustment of the natural frequency of the air column in the channel is possible.
  • This formula allows a precise determination of the optimal length l of the channel for each operating range.
  • the adaptation of the length l of the channel as a function of the aerodynamic speed of the compressor leads to the fact that always forms a defined flow state in the channel, whereby the channel is maximally effective and the compressor stability is maximally increased. Since the aerodynamic speed is available to the engine computer, the control of the length l of the channel is very easy and reliable to implement. Since the length l of the channel is optimally adapted to all speeds, an improvement in the compressor efficiency is also to be expected.
  • Determining the maximum length of the channel ensures that the channel is not set too long.
  • Fig. 4a, 4b, 4c and 4d each show a part of a housing, which is designed as a compressor housing 2 in a jet engine, not shown, a rotor blade 4 and a channel 20 with a piston 30th
  • the compressor housing 2 encloses the compressor duct 3, which is circular in cross-section.
  • the compressor duct 3 contains rotor blades arranged radially on a shaft or rotor disk, not shown. In the Fig. 4a-d only one blade 4 is shown in each case.
  • the rotor blade 4 has a blade tip 40, an upstream leading edge 41 and a downstream trailing edge 42. Between the blade tip 40 of the blade 4 and the compressor housing 2, there is a gap 43 in the compressor duct 3.
  • the channel 20 is arranged in the region of the blade tip 40 of the blade 4.
  • the channel 20 has a first end 21 and a second end 22.
  • the first end 21 of the channel 20 opens in the region of the blade tip 40 of the blade 4 in the compressor passage 3 and in the gap 43.
  • the second end 22 of the channel 20 is clearly spaced from the first end 21 and closed by the adjustable piston 30.
  • This channel 20 can be arbitrary in number, extent and shape in the axial direction and in the circumferential direction. It can be any number of channels 20 of the four embodiments, which in the Fig. 4a-d shown are arranged on the circumference of the compressor housing 2.
  • further channels 20 may be arranged on the moving blades of further compressor stages.
  • Fig. 4a the first embodiment of the channel 20 is shown in the compressor housing 2.
  • the channel 20 extends in a straight line and radially to the inner periphery of the compressor housing 2.
  • the first end 21 of the channel 20 opens in the downstream region of the blade tip 40 of the blade 4 in the gap 43 between the blade tip 40 and the compressor housing.
  • Fig. 4b the second embodiment of the channel 20 is shown in the compressor housing 2.
  • the channel 20 is rectilinear and is inclined at an acute angle to the non-illustrated longitudinal axis of the compressor housing 2, wherein the apex of the angle points in the flow direction.
  • the first end 21 of the channel 20 opens in the upstream region of the blade tip 40 of the blade 4 in the gap 43 between the blade tip 40 and the compressor housing. 2
  • Fig. 4c the third embodiment of the channel 20 is shown in the compressor housing 2.
  • the channel 20 extends straight at the second end 22 and radially to the inner periphery of the compressor housing 2.
  • the first end 21 of the channel 20 extends arcuately, tapers in the direction of the compressor passage 3 and flows upstream of the leading edge 41 of the blade 4 just before the gap 43rd between the blade tip 40 and the compressor housing 2 in the compressor duct 3rd
  • Fig. 4d the fourth embodiment of the channel 20 is shown in the compressor housing 2.
  • the channel 20 extends only at the second end 22 in a straight line and parallel to the longitudinal axis of the compressor housing 2, not shown.
  • the first end 21 of the channel 20 extends arcuately, tapers in the direction of the compressor passage 3 and flows upstream of the leading edge 41 of the blade 4 just before the gap 43 between the blade tip 40 and the compressor housing 2 in the compressor passage 3rd
  • Fig. 5 is the third embodiment according to Fig. 4c shown enlarged for the channel 20 in the compressor housing 2.
  • the air flow 7 is fed to the compressor stage formed by the rotor blade 4 and the guide blade 5.
  • the compressed air stream 8 exits the compressor stage.
  • the channel 20 includes the first end 21 and the second end 22 in which the piston 30 is located.
  • the blade 4 includes the blade tip 40, the leading edge 41 and the trailing edge 42. Between the blade tip 40 and the compressor housing 2 is the gap 43.
  • the axial distance between the leading edge 41 and the trailing edge 42 at the blade tip 40 is the chord length l ax .
  • the position of the channel 20 may be between the trailing edge 42 of the blade 4 and 1.3 times the axial chord length l ax measured from the trailing edge 42. This area is in Fig. 5 characterized by l pos .
  • Fig. 6 is the fourth embodiment according to Fig. 4d shown enlarged for the channel 20 in the compressor housing 2.
  • the compressor housing 2, with the compressor duct 3, the rotor blade 4 and the duct 20 with the piston 30 are again visible.
  • the duct 20 comprises a center line 23, the first end 21 and the second end 22, in which the piston 30 is located.
  • the blade 4 comprises the blade tip 40, the leading edge 41 and the trailing edge 42.
  • the gap 43 is located between the blade tip 40 and the compressor housing 2.
  • the aerodynamic speed n results from the mechanical compressor speed divided by the root of the compressor inlet temperature. This aerodynamic speed n is available to the engine computer.
  • k is any natural number (0, 1, 2, ...) over which the length l of the channel 20 can be increased without negatively affecting its effect.
  • ⁇ is the isentropic exponent
  • R is the specific gas constant
  • z is the blade number of the blade ring on which the channel 20 acts on the flow.
  • the adjustment of the length l of the channel 20 is realized by means of the piston 30, which moves in the part of the channel 20 which lies between the minimum length l min and the maximum length l max of the channel 20.
  • the piston 30 serves to change the length l of the channel 20 in such a way that, according to equation (2), the length l appropriate to the current aerodynamic rotational speed n is set.
  • the channel 20 is designed such that the piston 30 fits, ie the channel 20 is rectilinear in this region and has a constant cross section.
  • the method of the piston 30 is controlled by the aerodynamic speed n of the compressor and realized by means of a suitable mechanism, for example electrically (eg by a stepping motor), hydraulically or pneumatically.
  • the length l of the channel 20 must be selected so that a standing wave is generated in it.
  • the movable piston 30 is moved between the minimum length l min and the maximum length l max of the channel 20.
  • the travel s of the piston 30 is, as described above, dependent on the aerodynamic speed n.
  • two quantities must be matched to one another. These are the blade rate of the blade ring to be controlled and the volume of the channel 20.
  • Each blade 4 of the blade ring surrounds a static pressure field. This moves past the first end 21 of the channel 20 and vibrates the air column in the channel 20.
  • the piston 30 makes it possible to vary the volume of the channel 20. Thus, the natural frequency of the air column in the channel 20 is changed.
  • the volume is now adjusted to the compressor speed in such a way that the blade repetition frequency coincides with a multiple of the natural frequency of the air column in the channel 20, a resonance occurs and a standing wave of maximum amplitude is formed in the channel 20.
  • the standing wave on the piston 30 shows a node, and the speed is zero.
  • the standing wave has a belly.
  • a pulsating mass flow which stabilizes the flow in the region of the blade tips 40 of the rotor blades 4, is formed at the first end 21 of the channel 20.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Physics & Mathematics (AREA)
  • Geometry (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP09150842.4A 2008-02-15 2009-01-19 Structuration de boîtier destinée à la stabilisation de l'écoulement dans une machine de traitement des écoulements Ceased EP2090786B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102008009604A DE102008009604A1 (de) 2008-02-15 2008-02-15 Gehäusestrukturierung zum Stabilisieren der Strömung in einer Strömungsarbeitsmaschine

Publications (3)

Publication Number Publication Date
EP2090786A2 true EP2090786A2 (fr) 2009-08-19
EP2090786A3 EP2090786A3 (fr) 2011-04-20
EP2090786B1 EP2090786B1 (fr) 2016-10-12

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EP09150842.4A Ceased EP2090786B1 (fr) 2008-02-15 2009-01-19 Structuration de boîtier destinée à la stabilisation de l'écoulement dans une machine de traitement des écoulements

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US (1) US8262351B2 (fr)
EP (1) EP2090786B1 (fr)
DE (1) DE102008009604A1 (fr)

Cited By (2)

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EP2434164A1 (fr) * 2010-09-24 2012-03-28 Siemens Aktiengesellschaft Traitement de carter variable
CN102700031A (zh) * 2011-03-28 2012-10-03 三一电气有限责任公司 风力发电机叶片制作过程中的加热方法及制作用加热装置

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US9567942B1 (en) * 2010-12-02 2017-02-14 Concepts Nrec, Llc Centrifugal turbomachines having extended performance ranges
CN104781519B (zh) * 2012-11-28 2017-06-23 博格华纳公司 具有流量放大器的涡流增压器的压缩机级
US11702945B2 (en) 2021-12-22 2023-07-18 Rolls-Royce North American Technologies Inc. Turbine engine fan case with tip injection air recirculation passage
US11732612B2 (en) 2021-12-22 2023-08-22 Rolls-Royce North American Technologies Inc. Turbine engine fan track liner with tip injection air recirculation passage
US11946379B2 (en) 2021-12-22 2024-04-02 Rolls-Royce North American Technologies Inc. Turbine engine fan case with manifolded tip injection air recirculation passages
CN114517794B (zh) * 2022-03-01 2024-07-09 大连海事大学 一种跨音速轴流压气机联合机匣处理结构

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Cited By (2)

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Publication number Priority date Publication date Assignee Title
EP2434164A1 (fr) * 2010-09-24 2012-03-28 Siemens Aktiengesellschaft Traitement de carter variable
CN102700031A (zh) * 2011-03-28 2012-10-03 三一电气有限责任公司 风力发电机叶片制作过程中的加热方法及制作用加热装置

Also Published As

Publication number Publication date
US20090208324A1 (en) 2009-08-20
EP2090786B1 (fr) 2016-10-12
EP2090786A3 (fr) 2011-04-20
DE102008009604A1 (de) 2009-08-20
US8262351B2 (en) 2012-09-11

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