EP2434163A1 - Compresseur - Google Patents

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Publication number
EP2434163A1
EP2434163A1 EP10179365A EP10179365A EP2434163A1 EP 2434163 A1 EP2434163 A1 EP 2434163A1 EP 10179365 A EP10179365 A EP 10179365A EP 10179365 A EP10179365 A EP 10179365A EP 2434163 A1 EP2434163 A1 EP 2434163A1
Authority
EP
European Patent Office
Prior art keywords
compressor
flow passages
channel wall
flow
channel
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Withdrawn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
EP10179365A
Other languages
German (de)
English (en)
Inventor
Dirk Mertens
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.)
Siemens AG
Original Assignee
Siemens AG
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 Siemens AG filed Critical Siemens AG
Priority to EP10179365A priority Critical patent/EP2434163A1/fr
Publication of EP2434163A1 publication Critical patent/EP2434163A1/fr
Withdrawn legal-status Critical Current

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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
    • F04D27/0207—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
    • 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
    • F04D29/40—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
    • 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 compressor having an annular flow channel which extends concentrically along a machine axis of the compressor and is bounded radially on the outside by a channel wall, wherein flow passages are provided in the channel wall for influencing the gap flow between the blades and the channel wall.
  • Gas turbines and their functions are well known.
  • the sucked by a compressor of the gas turbine air is compressed in this and then mixed in a burner with fuel.
  • the mixture flowing into a combustion chamber burns to a hot gas, which subsequently flows through a turbine connected downstream of the combustion chamber and, in the meantime, causes the rotor of the gas turbine to rotate due to its relaxation.
  • Due to the rotation of the rotor a generator coupled to the rotor is driven in addition to the compressor, which converts the mechanical energy provided into electrical energy.
  • Gas turbines are also used as aircraft engines.
  • the total pressure rise across the compressor is the sum of all incremental pressure rises across each stage (or all wreaths).
  • a stall may occur within the compressor on one or more blades, ie, the flow rate of the air in the main flow direction returns to a small amount or to zero in a part of a compression stage.
  • the energy transferred from the rotor to the air is not sufficient to convey it through the compressor stage and to produce the required pressure ratio of the relevant compressor stage.
  • the pressure ratio is the pressure increase occurring over the relevant stage of the compressor, based on the inlet pressure of the respective stage.
  • stall If the stall is not counteracted immediately, it may progress to a rotating stall and possibly even cause the entire airflow through the compressor to reverse direction, known as compressor-pumping.
  • compressor-pumping This particularly critical operating condition jeopardizes the blading and prevents sufficient supply of the combustion chamber with compressor air, so that a faulty operation of the gas turbine diagnosed and the machine must be switched off immediately. Consequently, the aforementioned flow phenomena are undesirable and must be avoided if possible during operation safely.
  • the channels of the casing treatment leading to the partial flows are inclined with respect to the machine axis or rotation axis in such a way that, viewed in the direction of rotation of the rotor, the removal position lies after the feed position at which the decoupled partial flow is returned to the main stream near the gap.
  • the longitudinal extent of the return flow channel is substantially transversely to the straight line of the blade tip side staggering angle, ie aligned approximately parallel to the machine axis.
  • the FR 2 325 830 a compressor housing with grooves introduced therein. Also through these grooves should a stall of the boundary flow and thus the pumping of the compressor can be prevented, wherein, however, the adjusting through the grooves current does not flow against the main flow, but with this.
  • the object of the invention is to provide a compressor whose structured boundary wall achieves a further increase in the operating range of the compressor and a reduction in the inclination of the compressor for flow separation. At the same time, the efficiency of the compressor should be further improved or raised to the original level of a compressor without structured boundary wall.
  • a compressor according to the invention comprises an annular flow channel which extends concentrically along a machine axis of the compressor and is bounded radially on the outside by a channel wall, wherein flow passages for influencing the gap flow between the rotor blades and the channel wall are provided in the channel wall and at least one of the dimensions of at least one Preferably, all flow passages can be changed and / or means for changing the size of the opening of at least one, preferably all flow passages are provided.
  • the invention recognizes that the flow passages present in the duct wall are in principle advantageous only if the compressor is operated comparatively close to the stability limit. If the distance to the stability limit is sufficiently large, the static "Casing Treatment" has a rather negative effect. This then causes Störströmungen that reduce the efficiency of the compressor in this operating condition rather.
  • the invention thus proposes to activate the flow passages in the channel wall only in those operating conditions in which it is required.
  • the flow passages should not cause any aerodynamic effect.
  • at least one of the dimensions of at least one of the flow passages can be changed.
  • the volume and / or the contour of the flow passages are variable.
  • the flow passages are configured lockable.
  • a means for changing the size of the opening of at least one of the flow passages, preferably all flow passages is provided.
  • the relevant flow passages can be distributed uniformly along the circumference of the channel wall.
  • the respective flow passages are arranged only in one sector or in several sectors of the circumference. The restriction to one or more sectors is possible, since to disrupt a compressor operation restricting stripping or rotating stall it may be sufficient to disturb the phenomenon locally.
  • a structurally simple and inexpensive compressor can be specified.
  • flow passages relating to a plurality of axial sections of the flow channel are provided.
  • the compressor according to the invention which is usually designed as axial compressor is having a plurality of compressor stages, corresponding interference may occur at different compressor stages, so that it is advantageous to arrange the respective flow passages on the compressor stages usually involved in order to prevent the emergence and spreading of the disturbing phenomena early and on site.
  • the flow passages concerned are at least partially opposite the blade tips of blades of a blade ring of the compressor. This allows you to most effectively influence the gap flow between the tips of the blades of the blades and the channel wall.
  • the flow passages are three-dimensionally designed and accordingly have three dimensions: length (in the axial direction of the compressor), width (in the circumferential direction) and depth (in the radial direction).
  • the flow passage is cuboid or prism-shaped, both parallel to the machine axis or with respect to the machine axis inclined orientation.
  • the contour can also be designed bent.
  • steps or edges can be provided in each extension direction.
  • different contours - straight and curved - be combined in an extension direction.
  • the flow passages may also be inclined with respect to the radial direction or may extend mainly in the circumferential direction.
  • the respective flow passages are configured as holes penetrating the channel wall with, for example, a rectangular, parallelogram or ring segment-shaped cross section, in each of which a correspondingly contoured plug element is displaceably arranged to change the depth of the relevant flow passage.
  • a particularly simple construction is given, in which the depth of the flow passages is variable as a variable measure.
  • the depth of the flow passage can also be set to zero by means of the plug element so that the relevant flow passage is completely closed or no longer present. This operating position of the plug member is preferred for rated operation and adjacent operating conditions of the compressor.
  • the plug member may be moved out of the hole to first create a low depth flow passage which then increases outwardly with increasing displacement of the plug member. This is then possible until a maximum depth of the flow passages is reached.
  • the maximum depth is preferably reached only when the distance to the stability limit of the compressor has reached the minimum permissible value. Consequently, the patterning can be dynamically adjusted to the operation of the compressor to keep flow losses low overall.
  • the plug element is designed as a punch with a collar, which punch is inserted from radially outside into the hole of the channel wall.
  • the collar By using the collar, the maximum penetration depth of the plug element is limited in the relevant hole, so that a Hininragen the plug element can be safely avoided in the flow channel. This prevents the rubbing and damaging of the compressor blades passing the holes of the flow passage on the plug member.
  • the plug element is biased by means of a spring element.
  • the plug element is in a first end position, from which it can be moved with a drive to other positions while increasing the spring preload.
  • the provision of the plug element is then always by the spring force of the spring element, which is particularly desirable in case of failure of the drive.
  • the relevant flow passages are not formed as holes with a variable plug element, but as blind hole-like grooves, the groove opening by means of a displaceable in the circumferential direction cover, which also has openings, are exposable or closable.
  • the contour of the openings of the cover and the distance between them correspond to the Nutö Stammskontur and the distance between the grooves.
  • a stationary gas turbine provided for generating energy is equipped with a compressor of the aforementioned embodiment.
  • an aircraft engine can be configured with such a compressor.
  • FIG. 1 shows a construction variant of a gas turbine 1 in a longitudinal partial section. It has inside a rotatably mounted about a machine axis 2 rotor 3, which is also referred to as a turbine runner. Along the rotor 3 successive an intake 4, a compressor 5, a toroidal annular combustion chamber 6 with a plurality of rotationally symmetrical to each other arranged burners 7, a turbine unit 8 and an exhaust housing 9.
  • the annular combustion chamber 6 surrounds a combustion chamber 17 which is connected to an annular hot gas duct 16 , There four successively connected blade stages 10 form the turbine unit 8. Each blade stage 10 is formed of two blade rings.
  • a hot gas 11 produced in the annular combustion chamber 6 follows in the hot gas duct 16 each of a row of vanes 13 formed by a blade 15 row 14.
  • the vanes 12 are attached to the stator, whereas the blades 15 a row 14 each by means of a disc 19 on the rotor 3 are attached.
  • a generator or a working machine (not shown) is coupled.
  • each blade stage 10 is formed from a blade row 14 and one of them downstream arranged guide blade row 13.
  • the rotor blades 15 are attached to a disc 19 of the rotor 3 in the compressor 5.
  • the tips of the blades 15 are gap-forming a channel wall 20 opposite, which is arranged concentrically to the machine axis 2 of the gas turbine 1.
  • the inwardly facing surface of the channel wall 20th limits the axially extending flow channel 22 of the compressor 5 radially outward.
  • the channel wall 20 may be formed either as a guide blade carrier or as a housing.
  • FIG. 1 In the inwardly facing surface of the channel wall 20 are in FIG. 1 structures not shown further introduced, which are at least partially opposite the tips of the blades 15 and are known in principle as casing treatment.
  • the inventive design of these structures and their mode of action are described in detail in the following figures.
  • FIG. 2 - FIG. 5 show a first embodiment for changing the dimension of a flow passage.
  • FIG. 2 shows the cross section through the compressor 5 of the gas turbine 1 in the axial section of blades 15, which are arranged on the rotor 3 in a ring.
  • the tips 24 of the blades 15 is the annular channel wall 20 at a distance opposite.
  • a sector of the annular channel wall 20 a plurality of holes 26 is shown along the circumference, in each of which a radially displaceable plug element 28 is seated.
  • the number of holes 26 then corresponds to the number of blades 15 in the blade ring or a multiple thereof.
  • the holes 26 together with the plug elements 28 to be provided in two or more sectors of the circumference.
  • a the channel wall 20 encompassing housing.
  • FIG. 3 and FIG. 4 show the cross section of a portion of the channel wall 20 with only one of the holes 26 and the plug member 28 disposed therein in detail.
  • the hole 26 has a rectangular contour in the embodiment shown. Accordingly, the in FIG. 5 shown in perspective Plug element 28 in addition to a collar 29, a filling member 31 for closing the hole 26th
  • FIG. 3 shows the plug member 28 in a first position. In this first position, the plug member 28 completely closes the hole 26. As a result, the inner surface of the channel wall 20 has a stepless and edge-free course along the circumference in the region of the hole 26. Thus, there is no structuring at this point that affects the flow between the tips 24 of the blades 15 below the channel wall 20.
  • the displacement of the plug element 28 to the outside was carried out by a drive not shown.
  • the drive can be designed, for example, electrically, pneumatically or hydraulically. Other types of drive, such as piezoelectric actuators are also possible.
  • a helical spring 30 is provided, which is supported on a housing wall 33 of the compressor 5 which likewise surrounds the channel wall 20 in a ring-like manner. Also conceivable are spiral or disc springs as well as a return adjustment, which takes place only by means of one of the drive types described.
  • FIG. 3 and FIG. 4 shown holes 26 extend along the radial direction 27. This is not mandatory.
  • the holes 26 can also be compared to the radial direction 27 by a fixed, arbitrary angle ⁇ ( FIG. 3 ), which is indicated by a hole center line 29. Accordingly, the plug elements 28 also designed displaceable along the hole center line 29.
  • the flow passages 32 distributed over the circumference or in segments may also be divided into groups of flow passages 32.
  • the holes 26 are aligned parallel to each other, the orientation of the holes of two different groups are inclined to each other. If the different orientation is required, the group arrangement simplifies the production of the holes. This lowers the manufacturing costs.
  • FIG. 5 is that from the 3 and FIG. 4 known plug element 28 shown in perspective. Shown is a massive embodiment of the plug member 28, whereby this reacts rather sluggish due to its mass to dynamic Strömungseinlene.
  • the dimensions C and D are identical according to the plug member 28 shown. Alternatively, it is also possible that the dimensions C and D are different in size.
  • the construction shown is suitable for adjusting at least one dimension of the flow passage 32.
  • plug elements 28 modified in their contour it is possible to change not only the depth of the flow passages 32 but also the width of the flow passages or their length. A displacement of the plug elements in the axial and / or circumferential direction is conceivable.
  • a second embodiment of a variable flow passage 32 is in the 6 and FIG. 7 shown.
  • FIG. 6 two identical sections through the longitudinal section of the compressor 5 in the axial section of blades 15.
  • the channel wall 20 is the tips 24 of the blades 15 with respect to radial gap forming.
  • a plurality of grooves 34 are uniform along the circumference distributed, of which only one is shown.
  • the number of grooves 34 preferably corresponds to the number of blades 15 in the blade ring. All grooves 34 have a substantially rectangular contour and thus a correspondingly contoured slot opening. Other contours, such as those in FIG. 8 are shown are of course also possible.
  • the axial length of the grooves 34 corresponds approximately to the length of the axial projection of the tips 24.
  • a cover 36 is provided between the tips 24 of the blades 15 and the grooves 34.
  • the cover 36 is in FIG. 7 shown in perspective and formed as a ring plate.
  • openings 38 are provided in the same number to the grooves.
  • the openings 38 have an identical contour as the slot openings. In the illustrated embodiment, therefore, the contours of the openings 38 are also rectangular.
  • the cover 36 is as indicated by the arrow 39 in FIG FIG. 7 indicated, rotatable about a not-shown drive in the circumferential direction, so that the openings 38 can be superimposed with the groove openings aligned. In FIG. 7 this is shown for the groove 34a.
  • the flow passages 32 formed by the grooves 34 are variable.
  • the cover 36 could also at one of the edges of each opening 38 radially outwardly projecting tabs 41 which protrude into the grooves 34.
  • the cover 36 could also at one of the edges of each opening 38 radially outwardly projecting tabs 41 which protrude into the grooves 34.
  • the width of the flow passage 32 upon rotation the cover 36 are changed in the circumferential direction.
  • tab 42 With arranged on the transverse edge of the openings 38 tab 42 can be changed in displacement of the cover 36 in the axial direction, the length of the flow passage 32. In order to ensure the displaceability of the cover 36, however, this has only one of the two types of tabs, either the tab 41 or the tab 42, on.
  • contours 38a-38d for the holes 26 and plug members 28 and / or for the grooves 34 and openings 38 are shown.
  • a contour 38b which is basically rectangular but provided with a kink is also possible, as is an arcuate contour 38c or a contour 38d which is inclined relative to the machine axis 2 and thus parallelogram-shaped.
  • modified contours are also conceivable.
  • circumferential grooves 44 running in the circumferential direction can also be provided in the channel wall 20 as a casing treatment.
  • Such circumferential grooves 44 and modifications thereof are in the FIGS. 9 to 15 and are described in more detail below.
  • FIG. 9 shown embodiment shows in the axial section of a blade ring three axially successive circumferential grooves 44 which are endlessly circulating. Each of these circumferential grooves 44 is closed by a ring formed from segments.
  • FIG. 12 shows rings of two segments 46a, three segments 46b or four segments 46c, which may be arranged in the circumferential grooves 44. Each segment 46 is movable in the radial direction, which is in FIG. 12 is illustrated with the help of the arrows shown there. By the displacement of the segments 46, 46a, 46b, 46c in the radial direction, the inwardly facing opening of the corresponding circumferential groove 44, in which the corresponding ring is seated, can be at least partially exposed ( FIG.
  • circumferential grooves 44 be they endless or groove sections, they may instead also, as in FIG FIG. 13 shown, slots 47 may be provided in the channel wall 20 to form flow passages 32.
  • the slots 47 completely penetrate the channel wall 20.
  • arc segments 48 By inserted from the outside into the channel wall 20 arc segments 48, the individual slots 47 can be completely or partially closed ie filled. If a plurality of slots 47 are arranged one behind the other in the axial direction A, there is the possibility that an arc segment 48 can close only one slot 47, several slots 47 or all slots 47.
  • the arc segments 48 are thus formed analogously to the plug elements 28 and can therefore be positioned in a similar manner or be driven and reset, without being discussed here in more detail.
  • the circumferential grooves 44 represent the flow passages 32 of the casing treatment. Due to the cylindrical channel wall 20 can be by means of axial direction in the axial direction A sliding covers 52, 54, the circumferential grooves 44 are closed. By the use of the cover 52, the circumferential grooves 44 are closed successively upon displacement of the cover 52. If 54 openings 58 with a corresponding axial distance are present in the insert, this can close all circumferential grooves 44 at the same time. Depending on the relative position of the insert 54 relative to the channel wall 20, the circumferential grooves 44 can be completely or partially closed.
  • the cover 54 has over the cover 52 has the advantage that a comparatively short axial displacement is required to cover all three circumferential grooves 44.
  • FIG. 15 shows a schematic perspective partial view of a conical channel wall 20 to the machine axis with segmented circumferential grooves 44 to form flow passages 32. Due to the conical channel wall 20, the cover 56 is displaceable only in the circumferential direction and not in the axial direction to change the size of the openings of the groove portions 47.
  • the in the FIG. 9 to FIG. 15 The embodiments shown have the particular advantage that the flow passages 32, which extend mainly in the circumferential direction, can now for the first time be considered as casing treatment.
  • the circumferential grooves 44, slots 47 or groove sections cause such large losses at rated load that their use in avoiding flow phenomena at partial load was unjustifiable. Since the elimination of this defect by deactivating the Casing treatments at nominal load and by activating the casing treatment when approaching the surge line now possible, the use of circumferential grooves 44 or slots 47 and sections thereof as Casing Treatment is economically feasible for the first time.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP10179365A 2010-09-24 2010-09-24 Compresseur Withdrawn EP2434163A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP10179365A EP2434163A1 (fr) 2010-09-24 2010-09-24 Compresseur

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Application Number Priority Date Filing Date Title
EP10179365A EP2434163A1 (fr) 2010-09-24 2010-09-24 Compresseur

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EP2434163A1 true EP2434163A1 (fr) 2012-03-28

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106837879A (zh) * 2017-03-31 2017-06-13 浙江理工大学 一种具有弧形缝的压缩机机匣及其回流引导方法
BE1028335B1 (fr) * 2020-05-20 2021-12-20 Safran Aero Boosters Sous-ensemble de compresseur basse pression d'une turbomachine d'aéronef

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB504214A (en) * 1937-02-24 1939-04-21 Rheinmetall Borsig Ag Werk Bor Improvements in and relating to turbo compressors
US2850227A (en) * 1954-12-03 1958-09-02 Gen Motors Corp Compressor air bleed-off valve
GB801771A (en) * 1957-02-27 1958-09-24 Gen Motors Corp Improvements in axial-flow air compressors
GB1357016A (en) * 1971-11-04 1974-06-19 Rolls Royce Compressor bleed valves
FR2325830A1 (fr) 1975-09-25 1977-04-22 Rolls Royce Perfectionnements aux carters de compresseurs de moteurs a turbine a gaz
GB2158879A (en) * 1984-05-19 1985-11-20 Rolls Royce Preventing surge in an axial flow compressor
WO1995010692A1 (fr) * 1993-10-15 1995-04-20 United Technologies Corporation Derivation active du flux aux extremites dans un passage de redresseur a aubes
EP0719907A1 (fr) 1994-12-29 1996-07-03 United Technologies Corporation Virole pour turbine à gaz
EP1286022A1 (fr) 2001-08-14 2003-02-26 United Technologies Corporation Traitement de l'enveloppe pour compresseurs
WO2009153510A1 (fr) * 2008-06-18 2009-12-23 Snecma Systeme de decharge d'air pour compresseur de turbomachine aeronautique

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB504214A (en) * 1937-02-24 1939-04-21 Rheinmetall Borsig Ag Werk Bor Improvements in and relating to turbo compressors
US2850227A (en) * 1954-12-03 1958-09-02 Gen Motors Corp Compressor air bleed-off valve
GB801771A (en) * 1957-02-27 1958-09-24 Gen Motors Corp Improvements in axial-flow air compressors
GB1357016A (en) * 1971-11-04 1974-06-19 Rolls Royce Compressor bleed valves
FR2325830A1 (fr) 1975-09-25 1977-04-22 Rolls Royce Perfectionnements aux carters de compresseurs de moteurs a turbine a gaz
GB2158879A (en) * 1984-05-19 1985-11-20 Rolls Royce Preventing surge in an axial flow compressor
WO1995010692A1 (fr) * 1993-10-15 1995-04-20 United Technologies Corporation Derivation active du flux aux extremites dans un passage de redresseur a aubes
EP0719907A1 (fr) 1994-12-29 1996-07-03 United Technologies Corporation Virole pour turbine à gaz
EP1286022A1 (fr) 2001-08-14 2003-02-26 United Technologies Corporation Traitement de l'enveloppe pour compresseurs
WO2009153510A1 (fr) * 2008-06-18 2009-12-23 Snecma Systeme de decharge d'air pour compresseur de turbomachine aeronautique

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106837879A (zh) * 2017-03-31 2017-06-13 浙江理工大学 一种具有弧形缝的压缩机机匣及其回流引导方法
CN106837879B (zh) * 2017-03-31 2023-07-04 台州瑞晶机电有限公司 一种具有弧形缝的压缩机机匣及其回流引导方法
BE1028335B1 (fr) * 2020-05-20 2021-12-20 Safran Aero Boosters Sous-ensemble de compresseur basse pression d'une turbomachine d'aéronef

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