EP2805059A1 - Procédé et dispositif pour stabiliser un flux de compresseur - Google Patents

Procédé et dispositif pour stabiliser un flux de compresseur

Info

Publication number
EP2805059A1
EP2805059A1 EP12815994.4A EP12815994A EP2805059A1 EP 2805059 A1 EP2805059 A1 EP 2805059A1 EP 12815994 A EP12815994 A EP 12815994A EP 2805059 A1 EP2805059 A1 EP 2805059A1
Authority
EP
European Patent Office
Prior art keywords
compressor
fluid stream
flow
flow channel
paddle wheel
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Withdrawn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
EP12815994.4A
Other languages
German (de)
English (en)
Inventor
Stefan Bindl
Marcel Stössel
Reinhard Niehuis
Bastian Muth
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 der Bundeswehr Muenchen
Original Assignee
Universitaet der Bundeswehr Muenchen
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 der Bundeswehr Muenchen filed Critical Universitaet der Bundeswehr Muenchen
Publication of EP2805059A1 publication Critical patent/EP2805059A1/fr
Withdrawn legal-status Critical Current

Links

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
    • 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
    • F04D29/684—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps by fluid injection
    • 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
    • F04D27/0215—Arrangements therefor, e.g. bleed or by-pass valves
    • 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
    • F04D27/0238—Details or means for fluid reinjection
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/60—Fluid transfer
    • F05D2260/601—Fluid transfer using an ejector or a jet pump
    • 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
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/10—Purpose of the control system to cope with, or avoid, compressor flow instabilities
    • F05D2270/101—Compressor surge or stall

Definitions

  • the present invention relates to a method and an apparatus for providing a fluid flow to a compressor system of a turbomachine, in particular for stabilizing a compressor flow in or on an aircraft engine.
  • Turbo compressors also called turbocompressors, are essential components of turbomachines, for example of aircraft engines, gas turbines in power plants or other process engineering plants.
  • An aircraft engine essentially comprises a compressor, a combustion chamber, a turbine and a discharge nozzle. These components are arranged one behind the other in the flow direction.
  • the task of the compressor is to compress ambient air sucked into the engine and pass it on to the combustion chamber.
  • the compressed air is mixed with fuel and ignited the mixture.
  • the expanding gas escapes and drives the turbine, which in turn is connected via a shaft to the compressor in order to drive it.
  • the expanding gas escapes through a thruster and generates the propulsion.
  • Compressors as used in aircraft engines, usually consist of a cylindrical housing, which defines a flow channel for the compressed air in its interior.
  • the housing includes an opening to the air inlet at its axially forward end and an opening to the air outlet preferably to the combustion chamber at its axially rearward end.
  • the shaft extends on the succession in the axial direction a plurality of turbine blades driven by the turbine are arranged.
  • Each paddle wheel consists of a plurality of substantially identical profiled paddles whose plane is inclined with respect to the axial direction. The blades turn around the Wave, it comes due to the geometry of the blades for air transport through the compressor passage, and the air downstream of the paddle wheel is or is compressed upstream of the air upstream of the paddle wheel. In operation, therefore, there is at each paddle wheel a certain compression ratio between the air pressure downstream of the paddle wheel and the air pressure upstream of the paddle wheel. This compression ratio depends, for example, on the impeller geometry and / or the rotational speed of the impeller.
  • multi-stage compressors are used in practice in which a plurality of paddle wheels are connected in series in the compressor passage in order to gradually compress the air flowing into the compressor to the desired pressure level.
  • Fig. 1 illustrates schematically such a separation of the flow in a compressor grid.
  • the incidence angles ⁇ change from blade profile to blade profile until, finally, a critical angle of incidence is achieved in the adjacent profile, which leads to a separation of the flow at this profile.
  • the deflection of the fluid causes the initially affected blade passage is now again sufficiently flowed and relieved, so that the separation and thus the blocking of the passage can be canceled.
  • the disturbance continues to the next blade and travels counter to the rotor rotation direction through the compressor grid.
  • Such a disturbance in which reduced mass flow areas circulate at a speed less than the rotor speed, is generally referred to as a rotating stall.
  • An effective way to stabilize the air flow through the compressor and counteract the rotating flow separation is to inject additional air in the blade tip region, as described, for example, in S. Bindl et al., Active Stall Elimination by Air Injection onto the Tip Region of Compressor Blades ", ISABE-2009-1 105, Proceedings of the 19th International Symposium on Air Breathing Engines, Montreal, September 2009.
  • the targeted injection of air ener- gizes and stabilizes the flow close to the housing can be taken from a higher compressor stage of the compressor, from another engine or from another external source, but when taken from another engine or a downstream compressor stage of the compressor decreases its efficiency, since the extracted air is no longer for the thrust generation Even with a recirculation On and an exploitation of the dethrottling effect in the removal of air in the rear compressor stages, it is expedient to limit the amounts of air. Otherwise, the following components of the engine are severely impaired in their efficiency. In addition, the bleed air from the downstream compressor stages due the compression already reach high temperatures to which the front compressor stages are often structurally not designed. The unwanted heating limits the recirculated air mass flow and therefore the stabilizing effect of the air injection.
  • the invention therefore has the object to provide an improved method and an improved device for stabilizing the flow of air through the compressor and thereby increase the efficiency of the compressor.
  • the invention relates to a method for providing a fluid flow to a compressor system of a turbomachine, wherein the compressor system comprises at least one compressor housing, in which at least one paddle wheel is arranged and which is flowed through by a compressor flow, with the steps of supplying a primary fluid Flow into a mixing area of the compressor system and feeding a secondary fluid stream from an outside area of the compressor housing into the mixing area so that the secondary fluid stream at least partially mixes with the primary fluid stream to a resulting fluid stream; Supplying the resulting fluid stream from the mixing zone into the compressor stream upstream of the paddle wheel in the direction of the paddle wheel.
  • the inventors have recognized that by supplying a secondary fluid stream from the exterior of the compressor housing, a primary fluid stream which is more densified than the secondary fluid stream may be accumulated, such that the resulting fluid stream equals the compressor flow in the range the paddle wheel effectively stabilized. Due to the supply of the secondary fluid flow, effective stabilization can be achieved even with a comparatively small primary fluid flow, so that the disadvantages described with reference to the prior art of a reduction in the efficiency of the dichtersystems and excessive heating of the front compressor stages are reduced.
  • the mixing of the primary fluid flow with the secondary fluid flow can be effected in such a way that the primary fluid flow promotes the secondary fluid flow, in particular promotes it by pulse exchange.
  • the secondary fluid stream in the mixing region may contact the primary fluid stream and be accelerated by the primary fluid stream, such that after at least partial mixing of the primary and secondary fluid streams, the resulting fluid stream is created. This effect is commonly referred to as the ejector effect.
  • the primary fluid stream passes through the mixing zone prior to being fed into the compressor stream above or upstream of the paddle wheel and, depending on the design of the compressor system and the flow velocity, can draw in a secondary fluid stream whose mass flow is a multiple of the primary mass flow.
  • the secondary fluid flow is supplied from outside into the mixing area, i. preferably via an external supply line and not through the upstream stages of the compressor system or through the main inlet opening of the compressor housing, and thus increases the mass flow available for stabilizing the compressor flow, without the efficiency of the compressor system decreasing.
  • the secondary fluid flow is different from the compressor flow.
  • the terms “upstream” and “downstream” with respect to the compressor flow to understand, from which the compressor housing is flowed through.
  • the upstream side of the paddle wheel is therefore that side which faces the input of the compressor system or an upstream compressor stage.
  • the downstream side of the impeller is the side of the impeller facing the outlet or a downstream compressor stage.
  • the paddle wheel separates that portion downstream of the paddle wheel from which the primary fluid stream is discharged from that portion upstream of the paddle wheel in which, after the admixture of the secondary fluid stream, the resulting fluid stream is fed back into the compressor stream.
  • these areas may also be defined by more than one paddle wheel or by a plurality of compressor units. be separated from each other.
  • the pressure difference between the region in which the primary fluid stream is discharged and the region in which the resulting fluid mixture is fed is then correspondingly higher, so that the flow velocity and the mass flow rate of the primary fluid stream increase accordingly. This can increase the ejector effect.
  • inside area and “outside area” of the compressor housing may in the context of the invention relate to a radial direction perpendicular to the housing axis or shaft of the compressor.
  • the inner area is then closer to the housing axis or axis of rotation of the shaft than the outer area and in particular comprises the flow channel for the compressor flow.
  • the exterior of the compressor housing includes the area outside the compressor housing or the environment in which the compressor system is operated.
  • the medium of the secondary fluid stream may be similar to the medium of the primary fluid stream.
  • both media can be air.
  • the primary fluid stream may be more densified than the secondary fluid stream.
  • the primary fluid stream is discharged from the compressor stream of the first turbomachine downstream of the paddle wheel. In this configuration, a portion of the compressor flow is thus recirculated as a primary fluid flow.
  • the primary fluid stream is derived from a compressor stream of another turbomachine.
  • This embodiment is particularly advantageous when the first turbomachine and the further turbomachine are each aircraft engines of an aircraft. Depending on the attitude, flow instabilities can often occur to varying degrees in the various engines of an aircraft.
  • the invention then makes it possible to stabilize the compressor flow of the first, more unstable engine by means of the ejector effect and a primary mass flow supplied from the compressor system of the second, more stable engine.
  • the second turbomachine may, for example, also be an auxiliary gas turbine of the aircraft.
  • the primary fluid flow can be supplied from an external pressure accumulator. This embodiment is particularly advantageous in an application of the invention in process engineering plants.
  • the primary fluid stream and / or the secondary fluid stream are introduced into the mixing area such that the resulting fluid stream at least partially occurs on the paddle wheel.
  • the resulting fluid flow can be targeted to the impeller.
  • the paddle wheel comprises a plurality of blades, and the resulting fluid stream is supplied to the compressor stream such that the resulting fluid stream impinges the paddle wheel in the region of the blade tips of the blades.
  • the resulting fluid flow is supplied to the compressor flow along an edge region of the compressor flow.
  • the resulting fluid flow may be supplied to the compressor flow along a peripheral region of the compressor flow or along a peripheral region of a flow passage defined by the compressor casing.
  • the direction of the resulting fluid stream is substantially coincident with the direction of the primary fluid stream.
  • the directivity of a fast and high pressure outflowing primary fluid flow can be used in this way to specifically target the blades, in particular the blade tips, of the blade wheel.
  • the mixing area may be at least partially outside the compressor housing and / or outside an outer wall of a flow channel defined by the compressor housing.
  • the mixing area is completely outside the Flow channel.
  • the resulting fluid flow from the mixing region can be conducted via a supply line into the compressor flow and in the direction of the impeller.
  • the mixing region lies completely outside the flow channel and is connected to the flow channel via openings in the outer wall of the flow channel.
  • the mixing region can also be located at least partially in a flow channel which is defined by the compressor housing.
  • This configuration has the advantage of facilitating the feeding of the resulting fluid flow into the compressor flow and toward the impeller.
  • such a system can be integrated with little effort into existing compressor housing.
  • the compressor housing defines a flow channel, wherein the mixing region is at least partially closed with respect to the flow channel.
  • the mixing region may comprise a mixing chamber, which is preferably at least partially closed with respect to the flow channel.
  • a closed mixing area promotes the ejector effect and the formation of a stable resulting fluid flow.
  • the mixing region comprises a plurality of mixing chambers, which are preferably arranged along a peripheral region of the compressor flow.
  • the feeding of the resulting fluid flow over a plurality of mixing chambers along the peripheral region of the compressor flow allows a particularly effective stabilization of the compressor flow in the edge region of the compressor housing.
  • the method comprises impinging the impeller at a predetermined angle, in particular a variable angle.
  • the resulting fluid stream may be oriented to impinge on the blade substantially perpendicularly or at an angle ⁇ to a blade axis of a blade of the blade wheel and / or at an angle ⁇ to a plane of the blade wheel.
  • An angle ⁇ of zero degrees may mean that the resulting fluid flow is directed in the direction of rotation of the blade.
  • An angle of 180 degrees may mean that the resulting fluid flow is directed counter to the direction of travel of the blade.
  • the angle ⁇ is preferably in a range of 20 ° to 160 °, and more preferably in a range of 90 ° to 140 °.
  • the angle may be varied depending on a rotational speed of the paddle wheel, preferably in a range of 20 degrees to 160 degrees, and more preferably in a range of 90 degrees to 140 degrees.
  • the air injection and thus the stabilization of the compressor flow can be adjusted exactly to the operating state of the compressor.
  • an admixing ratio of a quotient of a mass flow of the secondary fluid flow and a mass flow of the primary fluid flow is at least one, preferably at least three and particularly preferably at least ten.
  • An inventive device for providing a fluid flow to a compressor system of a turbomachine comprises a compressor housing which defines a flow channel in which at least one paddle wheel is arranged, and a first supply line for a primary fluid flow, wherein the first supply line has a first input for the primary fluid flow, and having a first output, wherein the first output is in fluid communication with the flow channel upstream of the impeller, and a second supply line for a secondary fluid flow, wherein the second supply line has a second input, which with a Exterior of the compressor housing in fluid Connection and having a second outlet, which is in fluid communication with the flow channel upstream of the impeller, wherein the first output and the second output are arranged such that the secondary fluid flow at least partially with the primary fluid flow to a directed to the paddle wheel resulting fluid flow mixes.
  • upstream and downstream in the context of the invention in relation to a compressor flow, which passes through the compressor housing of the compressor system during operation of the turbomachine.
  • the configuration of the compressor system or the impeller specifies the flow direction with which the compressor housing is flowed through during operation.
  • the first inlet downstream of the paddle wheel is in fluid communication with the flow channel of the turbomachine.
  • the first input is in fluid communication with a compressor stage of another turbo-machine.
  • the first input is in fluid communication with an external pressure source.
  • first output and the second output are arranged relative to each other such that the primary fluid stream promotes the secondary fluid flow, in particular promotes it by pulse exchange.
  • the second output may be arranged adjacent to the first output, in particular be arranged directly adjacent.
  • the first output and / or the second output are arranged in an edge region of the flow channel.
  • the first exit is directed to the paddle wheel so that the resulting fluid stream impinges on the paddle wheel.
  • the second supply line is separated from the flow channel, in particular different from the flow channel.
  • the first output is disposed within the flow channel.
  • the first output may be aligned in the direction of the paddle wheel.
  • the device comprises a mixing line, which has a third input and has a third output, wherein the third input faces the first output and the third output is in fluid communication with the flow channel.
  • the third outlet may be located in the flow channel and aligned in the direction of the impeller.
  • the mixing pipe can serve to connect a mixing region, in which the secondary fluid stream mixes with the primary fluid stream, to the flow channel and to align the resulting fluid stream with the blade wheel.
  • the mixing pipe can also serve as a diffuser.
  • the third input has a diameter D, and a distance a between the first output and the third input is at least -3 D, preferably at least 0 and more preferably at least 2 D, wherein a negative distance indicates that the third input is upstream of the first output.
  • the inventors have recognized that a particularly high mixing ratio can be achieved in this distance range.
  • the distance a is not greater than 5 D, preferably not greater than 4 D.
  • a ratio between a cross-sectional area of the third input and a cross-sectional area of the first output is at least 1 to 1, preferably at least 5 to 1 and particularly preferably at least 10 to 1. In one development of the invention, the ratio between the cross-sectional area of the third input and the cross-sectional area of the first output is not greater than 100 to 1, preferably not greater than 60 to 1 and particularly preferably not greater than 40 to 1.
  • the inventors have recognized that a particularly effective ejector effect and a high admixing ratio can be achieved with these cross-sectional ratios.
  • the first exit and / or the third exit are oriented substantially perpendicular to a blade axis of a blade of the paddle wheel and / or at an angle to a plane or axis of the paddle wheel.
  • the device may in particular be adapted to vary the angle as a function of a rotational speed of the paddle wheel, preferably in a range of 20 degrees to 160 degrees, particularly preferably in a range of 90 degrees to 140 degrees.
  • the device according to the invention may preferably have a plurality of first outlets and / or a plurality of second outlets, which are arranged along a circumferential region of the flow duct.
  • the first outputs and / or the second outputs may be arranged along an inner peripheral side of the compressor housing.
  • first and / or second outputs make it possible to direct the resulting fluid flow distributed over the entire edge region of the compressor flow or flow channel to the impeller, so that a particularly effective stabilization of the flow can be achieved.
  • a main injector can feed several injection nozzles.
  • the plurality of first outputs may be connected to a common first supply line for a primary fluid flow.
  • a plurality of first supply lines may be provided for the primary fluid flow, which are respectively in fluid communication with a pressure source, in particular with the flow channel downstream of the impeller, and provide primary fluid streams at the respective outlets.
  • the plurality of second outputs can be in fluid communication with an outer region of the compressor housing via a common second supply line or separate second supply lines.
  • the device according to the invention comprises a mixing region, which is in fluid communication with the flow channel upstream of the impeller and into which the first outlet and the second outlet flow.
  • the mixing area allows mixing of the secondary fluid flow supplied from the outside of the compressor housing with the e.g. downstream of the impeller from the compressor system tapped primary fluid flow to the resulting fluid flow, which can be passed from the mixing area in the compressor stream and in the direction of the paddle wheel.
  • the device according to the invention can therefore be characterized alternatively via this mixing region and its design.
  • the invention therefore also relates to a device for providing a fluid flow to a compressor system of a turbomachine with a compressor housing, which defines a flow channel in which at least one paddle wheel is arranged, and with at least one mixing region, which upstream of the paddle wheel with the flow channel is in fluid communication, and having a first supply line for a primary fluid flow, wherein the first supply line is in fluid communication at a first input to a pressure source and is in fluid communication at a first output to the mixing region, and to a second supply line for a secondary Fluid flow, wherein the second supply line is at a second input in fluid communication with an outer region of the compressor housing and is in fluid communication with the mixing region at a second output.
  • the first supply line is in fluid communication with the flow channel at its first inlet downstream of the impeller.
  • the first supply line is at its first input in fluid communication with a flow channel of another turbomachine.
  • the pressure source can also be an external pressure source.
  • the mixing region comprises a mixing chamber which lies at least partially within the flow channel.
  • the mixing chamber comprises a chamber wall which separates the mixing chamber from the flow channel.
  • the mixing area can also have a mixing chamber which lies at least partially in the compressor housing and outside the flow channel.
  • the mixing chamber can have a chamber outlet, which is preferably arranged within the flow channel.
  • the mixing region may include a mixing conduit having a third inlet and a third outlet, the third inlet facing the first outlet and the third outlet fluidly communicating with the flow channel, in particular in the flow channel and oriented towards the impeller is.
  • the third input may have a diameter D, and a distance a between the first output and the third input may be at least -3 D, preferably at least 0, and particularly preferably at least 2 D, with a negative distance indicating that the third input is upstream of the first output.
  • a is not greater than 5 D, preferably not greater than 4 D.
  • the third exit is oriented substantially perpendicular to a blade axis of a blade of the blade wheel and / or at an angle to a plane of the blade wheel.
  • the angle is preferably in a range of 20 ° to 160 °, more preferably in a range of 90 ° to 140 °.
  • the apparatus may be arranged to vary the angle as a function of a rotational speed of the paddle wheel, preferably to vary in a range of 20 degrees to 160 degrees, more preferably in a range of 90 degrees to 140 degrees.
  • the mixing chamber may be a chamber inlet area A e i n, formed by a cross-sectional area of the second output, and a Kammerauslass Chemistry A, formed by a chamber outlet, which is preferably disposed within the flow channel have, where Ain / A> 1, preferably A e i n / A from > 3 and particularly preferably A e i n / A from > 10.
  • the compressor system is an axial compressor.
  • the compressor can be used in particular in an engine, preferably in an aircraft engine.
  • Fig. 1 illustrates in a schematic representation the rotating flow separation in a compressor grid
  • FIG. 2 schematically illustrates the principle of ejector injection for stabilizing a compressor flow in accordance with an embodiment of the present invention
  • FIG. 3 shows a compressor system with a blow-in system for supplying a stabilizing fluid flow along the edge region of the flow channel in accordance with an embodiment of the present invention
  • Figure 4 illustrates, by means of a schematic cross-sectional view, the angular relationship between the blades of the paddle wheel and the impinging resultant fluid flow
  • Fig. 5 is a schematic sectional view of the blow-in system of the embodiment of Figs. 3 and 4; and Fig. 6 shows a schematic sectional view of an alternative injection system according to an embodiment of the present invention.
  • the method according to the invention or the device according to the invention for providing a resulting fluid flow to a compressor system will be described below using the example of a compressor system for an aircraft engine.
  • the invention is not limited to this application.
  • the use according to the invention of the ejector effect enables a stabilization of the compressor flow or a reduction of flow instabilities, as it is, for example, the rotating flow separation, in all conventional gas compressor systems.
  • These include in particular compressor systems, such as are used in large numbers in process engineering plants, in particular stationary gas turbines for power generation.
  • the invention is based on the finding that the single-bubble mass flow takes advantage of the ejector effect can increase many times at preferably constant recirculation onsstrom. As a result, improved stabilization of the compressor flow can be achieved even with comparatively small recirculation flows and thus low losses in efficiency.
  • the ejector effect is based on the fact that a fast primary mass flow accelerates and demands the surrounding fluid through a momentum transfer.
  • the ejector effect is characterized by the so-called mixing ratio ⁇ , the quotient of the secondary mass flow (sec) and the primary mass flow (prim), m sec
  • the mixing ratio ⁇ describes the efficiency of the ejector.
  • the ejector effect is used in various industrial applications. Detailed numerical simulations and experimental studies on the basic effect of ejectors are provided by the inventors in articles B. Muth et al, "Basic Study of the Ejector Effect, Part 1: CFD ", 47th AIAA / ASMI / SAE / ASEE Joint Propulsion Conference and Exhibit, 31.07.-03.08.2011, San Diego, and M. Stêtel et al .:” Basic Study of the Ejector Effect, Part 2 : Experimental Approach, ibid., But not in connection with the stabilization of a compressor flow. The invention is based on the new and surprising finding that an ejector effect can advantageously also be used to stabilize the compressor flow.
  • FIG. 1 The principle of using the ejector effect to increase the injection flow to a compressor system is shown in FIG.
  • the blow-in system 10 is arranged upstream of a paddle wheel 12 of a compressor stage, of which only the blades 14 are shown for the sake of clarity.
  • the impeller 12 is rotatably supported about a rotation axis A, which coincides with the symmetry axis of the compressor system.
  • the plane of the blades 14 (shown in section in FIG. 2) is inclined with respect to the direction A in each case.
  • the sparging system 10 directs a primary fluid stream 16 through a nozzle 18 toward the blades 14 of the paddle wheel 12.
  • the primary fluid stream 16 is withdrawn from the compressor system downstream of the paddle wheel 12 (not shown in FIG. 2).
  • the injection system 10 further comprises a supply line from the outer region of the compressor, of which only the output openings 20 are shown in FIG. Through the supply line and its outlet openings, the primary fluid stream 16 sucks a secondary fluid stream 22 as it flows out of the nozzle 18.
  • the secondary fluid stream 22 contacts the primary fluid stream 16 in a mixing tube 24 located between the outlet of the nozzle 18 and the blades 14 of the paddle wheel 12 and is accelerated by the primary fluid stream 16.
  • the mixing tube 24 can additionally act as a diffuser.
  • the primary fluid stream 16 and the secondary fluid stream 22 mix in the mixing tube 24 to a resulting fluid flow, which flows against the blades 14 of the impeller 12.
  • the ejector effect in which the primary fluid stream 16 conveys a secondary fluid stream 22 from the exterior of the compressor system, results in a significant increase in the overall mass flow of the injection and thus in an increase in the efficiency of the engine process.
  • FIG. 3 is a perspective, partially sectioned view of a compressor system of an aircraft engine with a blow-in system according to the invention.
  • a compressor system A turbomachine generally comprises a plurality of compressor stages with a multiplicity of paddle wheels 12 arranged along the flow passage or the common axis of rotation A, and respective downstream stators.
  • the basic structure of such a compressor system as described in the introduction with reference to the prior art, is known in the art and not shown in detail in Fig. 3 for reasons of clarity.
  • the compressor system comprises a substantially cylindrical compressor housing 26, which defines in its interior a flow channel 28, which is flowed through by the compressor stream 30 in operation.
  • the paddle wheel 12 is rotatably mounted with the blades 14.
  • the blade surfaces are inclined relative to the axis of rotation A of the paddle wheel 12.
  • the impeller 12 is rotated and promotes due to the profiling of the blades 14, the air entering the flow channel 28 toward a downstream downstream stator or to subsequent compressor stages, so that a compressor flow 30 through the flow channel 28 sets.
  • the air is compressed so that the pressure downstream of the impeller 12 exceeds the pressure upstream of the impeller.
  • the primary fluid stream 16 downstream of the impeller 12 is branched off from the compressor stream 30 and returned to a mixing region upstream of the impeller 12 via first supply lines 32, which are partially disposed in the compressor housing 26.
  • the mixing area comprises a plurality of mixing chambers 34 which are arranged at equidistant intervals along a circumference of the inner wall of the compressor housing 26.
  • Each of the mixing chambers 34 includes inlet openings 20 for a secondary fluid stream 22 which the primary fluid stream 16 draws from the exterior of the compressor housing 26.
  • the structure and the configuration of the mixing chambers can be seen in the enlarged detail of FIG. 3 in more detail.
  • the mixing chambers 34 comprise a mixing chamber wall 36, which closes off a chamber interior in relation to the flow channel 28.
  • the output of the first supply line 32 opens into the chamber interior, in which the primary fluid stream 16 mixes with the secondary fluid stream 22.
  • the resulting fluid stream is directed via chamber outlet openings 38 at a predetermined angle towards the paddle wheel 12 so that it flows against the paddles 14.
  • the cam- it is also possible for the outlet openings 38 to be adjustable, so that the blades 14 of the blade wheel 12 can flow at different angles.
  • FIG. 4 illustrates the angular relationship during the flow of the blades 14 on the basis of a sectional drawing along the line B-B of FIG. 3.
  • the blade wheel 12 rotates along a direction of rotation U in a circulation plane 40, which lies perpendicular to the shaft axis A or to the compressor flow 30.
  • the blades 14 are inclined with respect to the orbital plane 40 by an angle ⁇ , which may depend on the configuration of the compressor system and the compressor stage.
  • the resulting fluid flow provided from the mixing chambers 34 via the chamber outlet openings 38 flows the blades 14 of the blade wheel 12 substantially perpendicular to a blade axis 42 and at an angle ⁇ to the orbital plane 40 of the blade wheel 12.
  • the adjustable chamber outlet openings 38 make it possible to select or vary the inflow angle ⁇ as a function of the rotational speed of the blades 14 and / or the operating state of the compressor system, in order to allow dynamic stabilization of the compressor flow 30 in this way.
  • the resulting fluid flow can be directed onto the blades 14 with a component in the running direction or else with a component counter to the running direction.
  • the inflow angle ⁇ can be varied in a range from 20 ° to 160 °, particularly preferably in a range from 90 ° to 160 ° and in particular in a range from 90 ° to 140 °.
  • the chamber outlet openings 38 are arranged such that the airfoils 14 are flowed in the axial direction.
  • the chamber outlet openings 38 can also be aligned in such a way that the airfoils 14 are flown at an angle ⁇ (not shown), measured in the radial direction to the blade axis 42.
  • the angle ⁇ is in the range between 45 ° and 135 °.
  • the plurality of mixing chambers 34 arranged along the peripheral region of the flow channel 28 make it possible to feed the stabilizing ejector stream almost uniformly over the entire peripheral region of the blade wheel 12 and thus to allow it to flow in the blade tip.
  • FIG. 5 shows the injection apparatus described above with reference to FIGS. 3 and 4 in a schematic cross-sectional drawing.
  • the limited by a housing wall of the compressor housing 26 flow channel 28 is flowed through in the illustration of FIG. 5 in the operation of the compressor system from left to right of the compressor stream 30.
  • a plurality of paddle wheels 12, 12 ', 12 " which correspond in their structure and function to the paddle wheel 12 described with reference to FIG. 3, are connected in series in the flow direction
  • the paddle wheels 12, 12 ', 12 "downstream of each can be downstream, are not shown in Fig. 5 for reasons of clarity.
  • first primary fluid flow supply line 32 having a first input 44 for diverting the primary fluid flow 16 from the flow passage 28 downstream of the paddle wheels 12, 12 ', 12' ' entering at the inlet 44 primary fluid flow 16 outside the wall of the flow channel 28 on the paddle wheels 12, 12 ', 12 "over and then through the wall of the flow channel 28 through a deflection portion 46 and an outlet 48, which may be formed as a nozzle into the mixing chamber 34, which is formed upstream of the impeller 12 on the inside of the wall of the compressor housing 26 and is separated by the mixing chamber wall 36 against the flow channel 28.
  • the primary fluid flow 16 exits the outlet opening 48 in the direction of the blade tip region of the blade wheel 12.
  • the outlet opening 38 of the mixing chamber 34 forms a mixing tube 24, the inlet opening 50 of the outlet opening 48 is preferably opposite concentrically and the output opening 52 is directed in the direction of the blade tips of the impeller 12.
  • the mixing chamber 34 is in fluid communication with an outside area of the compressor housing via a second supply line 54.
  • the high-velocity exit from the nozzle 48 primary fluid flow 16 sucks via the second supply line 54 air from the outer region of the compressor housing 26 as a secondary fluid stream 22 in the mixing chamber 34.
  • the secondary fluid stream 22 comes into contact with the primary fluid flow 16, is accelerated by the primary fluid flow 16 and mixed with him to a resulting fluid flow 56, which the mixing tube 24 through the output port 52 in Direction of the paddle wheel 12 leaves.
  • the mixing tube 24 may act as a diffuser and has a cross-sectional area which exceeds the cross-sectional area of the output 48 of the first lead 32 by 2 times, preferably more than 2 times or more.
  • the distance between the output 48 of the first supply line 32 and the inlet opening 50 of the mixing tube 24 is preferably in the range between 2 D and 4 D, wherein D denotes a diameter of the mixing tube 24.
  • D denotes a diameter of the mixing tube 24.
  • the distance a can be made smaller.
  • the output 48 of the first supply line 32 can also project into the mixing tube 24, so that the distance becomes negative. The compactness of an aircraft engine can severely limit the ratio.
  • the mixing tube 24 may include at its output port 52 movable parts (not shown) to direct the resulting fluid stream 56 to the blades 14 of the paddle wheel 12 at a predetermined angle ⁇ , depending on the operating state of the compressor system, as previously described with reference to FIG Figures 3 and 4 has been described.
  • Fig. 6 shows an alternative embodiment of a compressor system according to the invention, which is substantially similar to the embodiment described above with reference to Fig. 5 and differs only in the design of the mixing region.
  • the mixing region in the embodiment of FIG. 6 is at least partially outside the flow channel 28 and within the compressor housing 26.
  • the first supply line 32 opens into this Configuration within the compressor housing 26 into the mixing chamber 34.
  • the primary fluid stream 16 sucks a secondary fluid stream 22 via a second supply line (not shown) in the mixing chamber 34th
  • the mixing chamber 34 includes a mixing tube 24 'in which the secondary fluid stream 22 mixes with the primary fluid stream 16 to form the resulting fluid stream 56.
  • the mixing tube 24 passes through the wall of the compressor housing 26 and redirects the resulting fluid flow 56 in the direction of the impeller 12.
  • the mixing tube 24 'of the embodiment of Fig. 6 otherwise does not differ from the mixing tube 24, as previously described with reference to FIG.
  • An advantage of the configuration of FIG. 6, in which the mixing chamber is at least partially located outside the compressor housing 26, is that the sparging system requires no or minimal interference with the flow channel 28.
  • the chamber outlet openings 38 can only consist of slots in the wall of the flow channel 28, which are designed and arranged such that they guide the resulting fluid flow 56 in the direction of the impeller 12. This configuration has the advantage that the flow channel 28 remains completely free.

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

Abstract

L'invention concerne un système d'insufflation destiné au système compresseur d'une turbomachine, dans lequel un écoulement massique primaire recirculé ou provenant de l'extérieur transporte un écoulement massique secondaire hors de la zone externe du carter de compresseur en faisant appel à l'effet d'éjection, ce qui permet une stabilisation efficace du flux de compresseur et empêche le décrochage tournant sur les aubes de compresseur.
EP12815994.4A 2012-01-16 2012-12-20 Procédé et dispositif pour stabiliser un flux de compresseur Withdrawn EP2805059A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102012100339A DE102012100339A1 (de) 2012-01-16 2012-01-16 Verfahren und Vorrichtung zur Stabilisierung eines Verdichterstroms
PCT/EP2012/005308 WO2013107489A1 (fr) 2012-01-16 2012-12-20 Procédé et dispositif pour stabiliser un flux de compresseur

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EP2805059A1 true EP2805059A1 (fr) 2014-11-26

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US (1) US20140356128A1 (fr)
EP (1) EP2805059A1 (fr)
CN (1) CN104114875A (fr)
DE (1) DE102012100339A1 (fr)
WO (1) WO2013107489A1 (fr)

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RU2582537C2 (ru) * 2014-04-29 2016-04-27 Российская Федерация, от имени которой выступает Министерство обороны Российской Федерации Осевой компрессор
BE1023215B1 (fr) * 2015-06-18 2016-12-21 Techspace Aero S.A. Carter a injecteurs de vortex pour compresseur de turbomachine axiale
RU2679098C2 (ru) * 2016-08-01 2019-02-05 Алексей Анатольевич Пупынин Лопасть с каналом разрежения
US11655825B2 (en) * 2021-08-20 2023-05-23 Carrier Corporation Compressor including aerodynamic swirl between inlet guide vanes and impeller blades

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Publication number Publication date
CN104114875A (zh) 2014-10-22
WO2013107489A1 (fr) 2013-07-25
US20140356128A1 (en) 2014-12-04
DE102012100339A1 (de) 2013-07-18

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