EP3327258A1 - Roue de guidage d'entrée pour une turbomachine - Google Patents

Roue de guidage d'entrée pour une turbomachine Download PDF

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Publication number
EP3327258A1
EP3327258A1 EP17203272.4A EP17203272A EP3327258A1 EP 3327258 A1 EP3327258 A1 EP 3327258A1 EP 17203272 A EP17203272 A EP 17203272A EP 3327258 A1 EP3327258 A1 EP 3327258A1
Authority
EP
European Patent Office
Prior art keywords
blade
shroud
airfoil
radially
spindle
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Withdrawn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
EP17203272.4A
Other languages
German (de)
English (en)
Inventor
Frank Heinichen
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 EP3327258A1 publication Critical patent/EP3327258A1/fr
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/148—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of rotatable members, e.g. butterfly valves
    • 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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • 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
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • 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
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • F04D29/544—Blade shapes
    • 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
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/121—Fluid guiding means, e.g. vanes related to the leading edge of a stator vane
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/122—Fluid guiding means, e.g. vanes related to the trailing edge of a stator vane

Definitions

  • the invention relates to an inlet guide for a turbomachine according to the preamble of patent claim 1.
  • Compressors of aircraft engines are designed for a certain design speed.
  • the partial load range i. At speeds less than the design speed there is a risk of local flow separation on the rotor blades of the compressor grille.
  • a stator with adjustable stator blades in front of the first rotor of the compressor.
  • Such a stator is referred to as constraintsleitrad or Vorleitrad.
  • Variable-angle entry vanes improve the working range of a compressor.
  • the US 2010/0260591 A1 describes a compressor inlet guide, which consist of two radially spaced, each adjustable blade areas.
  • the EP 2 017 434 B1 describes a compressor inlet guide whose vanes are flexible in the axially rear region.
  • a radially outer rear region of the guide vanes is fixedly formed and a radially inner rear region of the guide vanes is flexible, wherein the two regions are rotatable independently of one another about a longitudinal axis by separate actuating means.
  • the present invention is based on the object to provide an inlet guide for a turbomachine with improved aerodynamic properties.
  • the invention contemplates an inlet guide for a turbomachine having a plurality of vanes extending circumferentially distributed radially in the flow channel of the turbomachine.
  • the vanes each have a first, radially outer airfoil and a second, radially inner airfoil.
  • the first, radially outer airfoil comprises a radially inner end
  • the second, radially inner airfoil comprises a radially outer end.
  • At least one of the blades is rotatably formed.
  • the invention provides that the first airfoil and the second airfoil are separated by a shroud that at least partially covers the radially inner end of the first airfoil and the radially outer end of the second airfoil.
  • the invention is thus based on the idea of the aerodynamic properties of a radially divided inlet guide, with radially inner and radially outer Vane is provided to improve by a shroud is provided, which covers the adjacent ends of the projecting into the flow channel airfoils and thereby on the one hand prevents flow leakage between the adjacent ends of the airfoils and the other turbulence at these ends of the airfoils.
  • the shroud encases the ends of the radially inner airfoils and the radially outer airfoils projecting into the flow channel.
  • the invention provides an improved part-load flow in the blade tip region of the rotor blades of the first rotor of a turbomachine arranged downstream of the inlet guide wheel. It thus enables a stability extension of a turbomachine under partial load conditions. It is applicable to inlet baffles of any turbomachinery, in particular inlet baffles of axial compressors, centrifugal compressors and turbines in aircraft engines and gas turbines.
  • the first airfoil is fixed locally and the second airfoil is rotatable relative to the first airfoil.
  • a rotation or adjustability of the staggering angle is thus provided only for the second, radially inner airfoil.
  • the solution according to the invention avoids, in particular, a flow leak, which would occur without the presence of a cover strip between the adjacent airfoils projecting into the flow channel, in particular if the radially outer airfoil and the radially inner airfoil have a different staggering angle.
  • the invention can in principle also be implemented with inlet guide vanes in which the first, radially outer airfoil and the second, radially inner airfoil are both independently rotatable and adjustable in their staggering angle, and more generally can also be realized with inlet guide wheels, in which only the first, radially outer airfoil is adjustable in its staggering angle.
  • a further embodiment of the invention provides that the shroud is connected to the first blade or integral, that is integrally formed therewith.
  • the shroud, the first airfoil and an outer shroud, with which the first airfoil can be arranged in an outer housing structure are integrally formed. Integral education prevents any gap between the shroud and the first airfoil.
  • the shroud covers the free end of the second radially inner airfoil.
  • the shroud and the first airfoil may be composed of individual components.
  • the shroud taken by itself may consist of one or more parts.
  • the second blade is rotatably connected to provide a rotatability with an outer spindle.
  • This can be operated from outside the inlet guide wheel. It is provided that the outer spindle is guided in a spindle bushing of the first blade, which is designed for example as a bore.
  • the first, radially outer airfoil thus serves to carry out the spindle necessary for the adjustability of the second airfoil.
  • the spindle axis which is equal to the axis of rotation of the second blade, extends in the radial direction. It can also be provided that the spindle axis extends inclined to the radial direction.
  • the spindle axis for the rotation of the second, radially inner airfoil can thus be designed either in a completely radial direction or inclined.
  • the inclined orientation may be associated with advantages with regard to the integration of a turntable in the shroud and with respect to the formation of a cutback at the trailing edge of the second airfoil, as will be explained.
  • x indicates the axial direction
  • r the radial direction
  • ⁇ the angle in the circumferential direction.
  • the axial direction is identical to the machine axis of a gas turbine, in which the turbomachine is arranged with the strictlyleitrad invention.
  • the radial direction points radially outward.
  • Terms such as “forward,” “behind,” “front” and “rear” refer to the axial direction
  • terms such as “outer” or “inner” refer to the radial direction.
  • a further embodiment of the invention provides that the outer spindle, which serves for the adjustability of the second, radially inner airfoil, has a spindle end projecting on the inside from the first airfoil, which end within the Deckbands arranged and stored in this.
  • the shroud thus receives the end of the spindle.
  • the second, radially inner airfoil is connected at its radially outer end with an outer circular platform or forms such, wherein the outer platform is arranged in the shroud and stored in this.
  • the circular platform forms a turntable which is connected to the spindle and serves for the rotatability of the second airfoil.
  • the shroud on the one hand on its radially outer side a circular hole for receiving and supporting the spindle end of the outer spindle and radially adjacent thereto and on its radially inner side a circular hole for receiving and supporting the outer Platform has.
  • the spindle end and the outer platform are both arranged in the shroud and stored.
  • the second airfoil has at its radially inner end an inner circular platform and an inner spindle.
  • the inner circular platform also forms a turntable for adjusting the second, radially inner airfoil.
  • the turntable and the inner spindle are arranged and mounted in an inner shroud of the inlet guide.
  • the circular platform together with the inner shroud forms the radially inner boundary of the flow channel through the inlet guide.
  • the inner spindle can not be actuated from the outside and serves only as a bearing. An adjustment of the airfoil is done solely by the outer spindle.
  • the shroud covers the radially inner end of the first blade and the radially outer end of the second blade so that no gap between the radially inner end of the first blade and the shroud, at least in the region of the leading edge of the blades and no gap is formed between the radially outer end of the second blade and the shroud. At least at and adjacent to the leading edge of the airfoils, free shroud ends and associated turbulence are thus avoided by the shroud.
  • An embodiment of the invention provides that the second blade in the region of its trailing edge adjacent to the shroud a pruning such has, that it forms a gap to the shroud in the region of its trailing edge.
  • the second airfoil in the region of its trailing edge adjacent to a radially inner flow channel boundary also has a cutback such that it forms a gap to the radially inner flow channel boundary in the region of its trailing edge.
  • the first blades and the second blades are designed in such a way and the second blades are adjustable in the partial load range with respect to the staggering angle that the second blades cause a stronger acting on a flowing working fluid with swirl than the first blades. This ensures that the rotor blades of a rotor arranged downstream of the inlet guide wheel are flown in the radially outer region with a higher axial velocity, whereby the risk of flow separation and vibration excitations is reduced.
  • An embodiment of the invention provides that the second airfoils extend in the radial direction over a length which corresponds to at least 50%, in particular at least 60%, in particular at least 70% of the total length of the radial extent of the first and second airfoils.
  • the flow channel formed as an annular space is divided radially in the region of the inlet guide by the first and second blades into two flow areas, a radially inner flow area and a radially outer flow area.
  • the swirl which is given to the working fluid by means of the guide vanes, is adjustable by means of the adjustable second airfoils. These should extend over at least 50% of the radial extent of the entire airfoil.
  • the shroud is formed as an element which is arranged in the flow channel, aerodynamically resistant. Accordingly, it is contemplated that it includes a rounded leading edge and a rounded trailing edge.
  • the shroud is designed according to an embodiment as a shroud ring, which separates the first blade and the second blade in all the guide vanes of the inlet guide and thereby projecting into the flow channel radial ends of the At least partially covering airfoils.
  • the shroud ring extends in a circular manner in the inlet guide wheel, at a radial distance from the radially outer flow channel boundary and at a radial distance from the radially inner flow channel boundary.
  • the shroud ring can consist of individual segments which are interconnected.
  • the formation of the shroud as shroud ring is not mandatory.
  • the guide vanes which each have a first, radially outer airfoil and a second, radially inner airfoil, are each assigned a separate cover band.
  • the shroud extends in this case only to such an extent in the circumferential direction that it can cover the projecting into the flow channel blade ends.
  • the shroud is designed for this case similar to a loom shuttle.
  • the guide vanes of the inlet guide wheel extend in the flow channel of the turbomachine between a radially outer flow channel boundary and a radially inner flow channel boundary.
  • the radially outer flow channel boundary is formed, for example, by a housing device which delimits the flow channel radially through the turbomachine on the outside and to which the guide vanes of the inlet guide wheel are fastened.
  • a housing device which delimits the flow channel radially through the turbomachine on the outside and to which the guide vanes of the inlet guide wheel are fastened.
  • an outer shroud or Genosusedeckband that connects the radially outer blades are arranged and fixed in such a housing device.
  • the radially inner flow channel boundary of the turbomachine is formed for example by corresponding ring surfaces of the rotors and stators of the respective compressor or turbine stages or a rotor drum of the corresponding drive shaft.
  • the invention further relates to a turbomachine, in particular a compressor with an inlet guide wheel according to claim 1, wherein the inlet guide is arranged upstream of the first rotor of the turbomachine or of the compressor.
  • FIG. 1 1 schematically shows a turbofan engine 100 having a fan stage with a fan 10 as a low-pressure compressor, a medium-pressure compressor 20, a high-pressure compressor 30, a combustion chamber 40, a high-pressure turbine 50, a medium-pressure turbine 60 and a low-pressure turbine 70.
  • the medium-pressure compressor 20 and the high-pressure compressor 30 each have a plurality of compressor stages, each comprising a rotor and a stator.
  • the turbofan engine 100 of FIG. 1 further comprises three separate shafts, a low pressure shaft 81 connecting the low pressure turbine 70 to the fan 10, a medium pressure shaft 82 connecting the medium pressure turbine 60 to the intermediate pressure compressor 20, and a high pressure shaft 83 connecting the high pressure turbine 50 to the high pressure compressor 30.
  • this is only to be understood as an example.
  • the turbofan engine did not have a medium pressure compressor and medium pressure turbine, only a low pressure shaft and a high pressure shaft would be present.
  • the turbofan engine 100 has an engine nacelle 1 (also referred to as engine cowling) which includes an inlet lip 14 and internally forms an engine intake 11 which supplies incoming air to the fan 10.
  • the fan 10 has a plurality of fan blades 101 connected to a fan disk 102.
  • the annulus of the fan disk 102 forms the radially inner boundary of the flow path through the fan 10. Radially outside the flow path is limited by a fan housing 2. Upstream of the fan disk 102, a nose cone 103 is disposed.
  • the turbofan engine 100 forms a secondary flow channel 4 and a primary flow channel 5.
  • the primary flow channel 5 passes through the core engine (gas turbine) comprising the medium pressure compressor 20, the high pressure compressor 30, the combustor 40, the high pressure turbine 50, the medium pressure turbine 60, and the low pressure turbine 70.
  • the medium-pressure compressor 20 and the high-pressure compressor 30 are surrounded by a peripheral housing 29, that on the inside forms an annular space surface which defines the primary flow channel 5 radially outward.
  • Radially inside, the primary flow channel 5 is bounded by corresponding ring surfaces of the rotors and stators of the respective compressor stages or by the hub or hub connected to the elements of the corresponding drive shaft.
  • a primary flow passes through the primary flow passage 5, which is also referred to as the main flow passage.
  • the secondary flow channel 4 also referred to as bypass duct, bypass duct or bypass duct, passes in the operation of the turbofan engine 100 by the fan 10 sucked air past the core engine.
  • the described components have a common axis of rotation 90.
  • the axis of rotation 90 defines an axial direction of the turbofan engine.
  • a radial direction of the turbofan engine is perpendicular to the axial direction.
  • a compressor of the aircraft engine having an input stator located upstream of the first rotor of the compressor.
  • a transformer located upstream of the first rotor of the compressor.
  • such a crossestrad could be formed in a turbine.
  • FIG. 12 schematically illustrates an entrance guide wheel 300 constructed in accordance with the principles of the present invention.
  • the inlet guide wheel 300 is arranged in a flow channel 5, which has a radially outer flow channel boundary 51 and a radially inner flow channel boundary 52.
  • the flow channel 5 is formed as an annular space. It may, for example, a primary flow channel corresponding to the primary flow channel 5 of FIG. 1 act.
  • the inlet guide 300 is arranged with respect to the axial direction in front of the first rotor 6 of a compressor stage of a compressor.
  • the inlet guide wheel 300 comprises a plurality of guide vanes 3, each having a first, radially outer airfoil 31 and a second, radially inner airfoil 32.
  • the radially outer airfoil 31 is fixed locally and accordingly has a fixed staggering angle.
  • the radially inner airfoil 32 is rotatable about an axis of rotation defined by the longitudinal axis of a spindle 35 and thus adjustable in its staggering angle.
  • the spindle 35 is accessible from outside the flow channel 5 and adjustable.
  • the first, radially outer airfoil 31 has a radially inner end 310, which protrudes into the flow channel 5, starting from the radially outer flow channel boundary 51.
  • the second, radially inner airfoil 32 has a radial outer end 320, which projects from the radially inner flow channel boundary 52 into the flow channel 5.
  • the inlet guide wheel 300 further comprises a shroud 7, which separates the first blade 31 and the second blade 32.
  • the shroud 7 covers the radially inner end 310 of the first blade 31 and the radially outer end 320 of the second blade 32 at least partially, in particular in the region of the leading edges of the two blades 31, 32nd
  • the second airfoil 32 is rotatable relative to the first airfoil 31 and adjustable in its staggering angle.
  • the spindle 35 is guided by the first blade 31, which, for example, forms a bore for this purpose.
  • the first blade 31 is accordingly formed with a sufficient thickness to accommodate the spindle 35 can.
  • the shroud 7 may further serve to receive storage and adjustment elements of the second blade 31, as will be explained with reference to the following figures with reference to embodiments.
  • the inlet guide wheel 300 comprises a plurality of such guide vanes 3, which are arranged distributed in the circumferential direction in the flow channel 5.
  • the guide vanes 3 are arranged, for example, in a housing device (not shown separately), which forms the radially outer flow channel boundary 51.
  • the Figures 3 . 4a-4c . 5a-5c and 6a-6b show an embodiment of a strictlysleitrads 300.
  • the demandingsleitrad 300 is located as shown in the FIG. 2 in a flow channel 5, which has a radially outer flow channel boundary 51 and a radially inner flow channel boundary 52.
  • the inlet guide wheel 300 is located in front of the first rotor 6 of a compressor.
  • the inlet guide wheel 300 has a multiplicity of guide vanes 3 which are distributed in the circumferential direction in the annular space formed by the flow channel 5 are arranged. It comprises a housing cover strip 37, with which it is arranged in the region of the radially outer flow channel boundary 51 in a housing device, not shown.
  • the inlet guide wheel 300 further comprises an inner shroud 38, which forms the radially inner flow channel boundary 52 in the region of the inlet guide wheel 300.
  • the inlet guide 300 may be formed without inner shroud 38, for which case the guide vanes 3 form a gap to the radially inner flow channel boundary 52.
  • the guide vanes 3 extends in the flow channel 5 in the radial direction r between the housing cover strip 37 and the inner cover strip 38. It comprises a first, radially outer airfoil 31 and a second radially inner airfoil 32.
  • the first, radially outer airfoil 31 is fixed locally and not adjustable in its stagger angle.
  • the second, radially inner airfoil 32 is adjustable and adjustable in its staggering angle.
  • it has an outer circular platform 33, which forms a turntable and is connected to a spindle 35, via which from outside the flow channel 5 of the staggering angle of the second blade 32 is adjustable.
  • the spindle 35 is guided in a spindle guide 311 in the first blade 31.
  • the second, radially inner airfoil 32 further includes an inner circular platform 34 which forms another turntable and which is connected to an inner spindle 36, which is mounted in the inner shroud 38.
  • the inner platform 34 at least partially delimits the flow channel 5 in the region of the radially inner flow channel boundary 52.
  • the inlet guide wheel 300 further comprises a shroud 7, which extends annularly in the flow channel 5 and which separates the first blade 31 and the second blade 32 in the radial direction.
  • the shroud 7 is aerodynamically resistant to resistance and has a rounded front edge 71 and a rounded trailing edge 72. It also has a radially outer top 75 and a radially lower bottom 76, see.
  • Figures 6a and 6b
  • the shroud 7 is fixedly connected to the first blade 31 or formed integrally therewith.
  • the shroud 7 and the first blade 31 have been produced in a manufacturing process and accordingly consist of the same material.
  • the shroud 7 is thus rotatably connected to the first blade 31 and via this and the GeHousedeckband 37 fixed to structural components of the outer flow channel boundary 51, for example, a housing device connected.
  • An embodiment variant provides that the shroud 7, the first blade 31 and the housing cover strip 37 are integrally formed.
  • the shroud 7 covers both the radially inner end 310 of the first airfoil 31 and the radially outer end 320 of the second airfoil 32.
  • Such a cover can, as directly from the FIG. 3 in such a way that, at least in the region of the leading edges of the blades 31, 32, no gap is formed between the radially inner end 310 of the first blade 31 and the shroud 7 and no gap between the radially outer end 320 of the second blade 32 and the shroud 7 are.
  • the shroud 7 further serves to receive and store components of the second airfoil 32.
  • the shroud 7 has on its upper side 75 a circular hole 73 for receiving and supporting the end 351 of the spindle 35, cf. Figures 3 and 6a, 6b , Furthermore, it has on its underside 76 a circular hole 74 for receiving the outer platform 33 of the second airfoil 32.
  • the shroud 7 thus fulfills, in addition to its function, by covering the projecting into the flow channel 5 ends 310, 320 of the blades 31, 32 to prevent leakage and turbulence at these blade leaves ends, the function, storage and adjustment for the adjustability of the second Shovel sheet 32 to record and store.
  • the second airfoil 32 in the region of its trailing edge 323 radially adjacent to the shroud 7 and radially adjacent to the radially inner flow channel boundary 52 cutbacks 321, 322, which ensure that the second airfoil 32 in its axially rear region one Gap to the shroud 7 and a gap to the radially inner flow channel boundary 52 forms, thereby preventing that in an adjustment of the second airfoil 32, this collides with the inner shroud 7 or the radially inner flow channel boundary 52.
  • the shroud 7 extends annularly in the flow channel 5, wherein the FIG. 6a a section of about 45 ° in the circumferential direction shows.
  • the shroud ring 7 can be divided into interconnected segments. This also applies to the inlet guide in total.
  • the shroud 7 is not formed as a ring, but by circumferentially limited structures, which in each case in only one of the vanes or only some of the vanes, a separation of the first airfoil and the second airfoil in the manner described make.
  • the second airfoil 32 extends in the radial direction r over a length which corresponds to at least 50%, in particular at least 60%, in particular at least 70% of the total length of the radial extent of the two airfoils 31, 32.
  • the second airfoils 32 are adjusted in any case in the partial load range with regard to their staggering angle, such that the second airfoils 32 bring about a stronger impingement of a working fluid flowing through with a twist than the first airfoils 31. This ensures that the rotor blades of the downstream of the inlet guide 300 arranged rotor 6 are flowed in the radially outer region with a higher axial velocity, whereby the risk of flow separation and vibration excitations is reduced.
  • FIG. 7 shows an embodiment which, except for the circumstance of the embodiment of the Figures 3 . 4a-4c . 5a-5c and 6a-6b corresponds to that the spindle axis for adjusting a radially inner airfoil is inclined to the radial direction r.
  • the inlet guide 300 of the FIG. 7 as well as the FIG. 3 a first, radially outer airfoil 31, a second, radially inner airfoil 32 and a shroud 7, which separates the first airfoil 31 and the second airfoil 32.
  • the second airfoil 32 includes an outer platform 33 and a spindle 35, via which the second airfoil 32 is adjustable with respect to its stagger angle, and an inner platform 34 and an inner spindle 36 which are mounted in a radially inner shroud 38.
  • the shroud 7 is fixedly connected to the first blade 31 and may be integrally formed therewith.
  • the axis of the spindle 35 is inclined to the radial direction r, wherein the angle between the spindle axis and the radial direction r, for example, is less than 30 °.
  • An inclination of the spindle axis may be associated with the advantage that the outer platform 33 can be arranged and stored more completely in the shroud 7 and the cutouts 321 and 322 in the rear region of the second blade 32 to the shroud 7 and the radially inner flow channel boundary 52 may be less pronounced ,
  • the flow channel 5 upstream of the inlet guide wheel 300 is shown with falling annulus lines. However, this is only to be understood as an example.
  • the flow channel 5 can also be provided with other courses and, for example, be formed in front of the inlet guide wheel 300 alternatively straight or with rising Annuluslinien.
  • the present invention is not limited in its embodiment to the embodiments described above.
  • the exact shape and configuration of the shroud 7 and its radial positioning in the flow channel 5 are only to be understood as examples.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Geometry (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP17203272.4A 2016-11-24 2017-11-23 Roue de guidage d'entrée pour une turbomachine Withdrawn EP3327258A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102016122696.3A DE102016122696A1 (de) 2016-11-24 2016-11-24 Eintrittsleitrad für eine Turbomaschine

Publications (1)

Publication Number Publication Date
EP3327258A1 true EP3327258A1 (fr) 2018-05-30

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EP17203272.4A Withdrawn EP3327258A1 (fr) 2016-11-24 2017-11-23 Roue de guidage d'entrée pour une turbomachine

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US (1) US20180142569A1 (fr)
EP (1) EP3327258A1 (fr)
DE (1) DE102016122696A1 (fr)

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DE102018117884A1 (de) * 2018-07-24 2020-01-30 Rolls-Royce Deutschland Ltd & Co Kg Strukturbaugruppe für einen Verdichter einer Strömungsmaschine
CN112283126A (zh) * 2020-12-15 2021-01-29 中国航发上海商用航空发动机制造有限责任公司 压气机和航空发动机

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