EP2123860B1 - Redresseur de tourbillons combiné - Google Patents

Redresseur de tourbillons combiné Download PDF

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Publication number
EP2123860B1
EP2123860B1 EP09158557.0A EP09158557A EP2123860B1 EP 2123860 B1 EP2123860 B1 EP 2123860B1 EP 09158557 A EP09158557 A EP 09158557A EP 2123860 B1 EP2123860 B1 EP 2123860B1
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EP
European Patent Office
Prior art keywords
bleed air
air tubes
hole passages
bleed
airflows
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.)
Not-in-force
Application number
EP09158557.0A
Other languages
German (de)
English (en)
Other versions
EP2123860A2 (fr
EP2123860A3 (fr
Inventor
Stefan Hein
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 EP2123860A2 publication Critical patent/EP2123860A2/fr
Publication of EP2123860A3 publication Critical patent/EP2123860A3/fr
Application granted granted Critical
Publication of EP2123860B1 publication Critical patent/EP2123860B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • 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
    • F01D17/105—Final actuators by passing part of the fluid
    • 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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • 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
    • F04D29/58—Cooling; Heating; Diminishing heat transfer
    • F04D29/582—Cooling; Heating; Diminishing heat transfer specially adapted for elastic fluid pumps

Definitions

  • the invention relates to a vortex rectifier for guiding bleed air streams. Moreover, the invention relates to a method for guiding extraction air flows by means of the vortex rectifier.
  • bleed air streams are branched from the air flow in the compressor to cool or seal certain components.
  • the bleed air streams are conveyed between two adjacent rotor disks of the compressor, e.g. in the sixth stage of the high-pressure compressor, for example, branched off through holes in one of the rotor discs of the compressor and flow through an intermediate disc chamber between the two rotor discs in the direction of the shaft.
  • vortex rectifiers are used.
  • the bleed air streams after passing through the inter-disk chamber, are directed along the shaft downstream into the area of the turbine to be there, e.g. to seal the spaces between the rotor disks of the turbine. Subsequently, the extraction air is passed into the gas stream.
  • Vortex Reducer Vortex Reducer
  • the advantage of a vortex rectifier is that the air does not experience an increase in its peripheral speed when flowing through the intermediate disc chamber to the shaft center and thus does not form a free vortex.
  • the concomitant pressure loss is lower than would be the case compared to a non-swirl reduced system.
  • a swirl rectifier which is formed from an annular bearing leg on one of the adjacent rotor disks of the compressor, a separate carrier ring and a plurality of bleed air tubes.
  • the carrier ring is fastened in the radially outer region to the adjacent rotor disks of the compressor.
  • the bleed air tubes are arranged in openings on the circumference of the carrier ring and directed radially inwardly toward the shaft. The openings in the carrier ring adjoin hole passages in the annular bearing leg.
  • the US 4,919,590 describes a vortex reducer formed of vanes formed radially on one of the rotor disks forming the inter-disk chamber. There are thus circular segment-shaped channels between the blades, which guide the extraction air flows in the intermediate disc chamber.
  • the invention is therefore based on the object to provide a vortex rectifier, for which little material is needed and therefore has a low weight, at the same time directed extraction air flows are generated with low pressure losses.
  • the solution of the problem in a vortex rectifier for guiding bleed air flows, which is arranged in an inter-disk chamber between two rotor disks of the compressor of a gas turbine with at least one shaft and at least one ring with circumferentially arranged first hole passages, second hole passages and extraction air tubes.
  • bleed air tubes are disposed only in the first hole passages with the bleed air tubes uniformly distributed around the circumference of the ring and the second hole passages being free of bleed air tubes, and first partial air flows through the first hole passages into the bleed air tubes and second partial air streams through the second hole passages into clearances are feasible between the bleed tubes.
  • This vortex rectifier thus has a combination of first hole passages with bleed air tubes and second hole passages without bleed air tubes.
  • the combined vortex rectifier requires less material and thus has a lower weight than the prior art tube type vortex rectifiers.
  • the formation of a free vortex is prevented in the intermediate disc chamber, whereby a swirl reduction is ensured.
  • the vortex rectifier is less susceptible to wear than the vortex rectifier EP 1 457 640 B1 or EP 1 564 373 B1 because it has a lower number of bleed air tubes.
  • the centrifugal forces acting on the ring are lower than in these two prior art embodiments.
  • the first hole passages with bleed air tubes comprise one-third and the second hole passages two-thirds of the total number of hole passages. This selection causes a significant reduction in weight while sufficient swirl reduction. However, another ratio between first and second hole passages can be selected.
  • the bleed air tubes are arranged in a straight line radially. This allows a particularly low-loss radial flow of the bleed air through the vortex rectifier.
  • the bleed air tubes may be curved against the direction of rotation of the compressor. This causes the partial airflows in the circumferential direction to enter the shaft channel at an angle of, for example, 45 ° to the radius and not be braked by a radial flow against the shaft.
  • the curvature against the direction of rotation of the compressor prevents the formation of swirl in the interstices of the vortex rectifier and in the wave channel.
  • the bleed air tubes have ribs which protrude into the spaces between the rotor discs. Through these ribs, the bleed air streams between the bleed air tubes can be further straightened.
  • the extraction air tubes are oval in cross-section. Due to the oval cross-section, the bleed air tubes fill the inter-plate chamber in the axial direction better. This prevents a portion of the bleed air from radially rotating past the bleed air tubes.
  • radial blades may be mounted on at least one of the two rotor disks, which project axially into the spaces between the extraction air tubes. Also by these blades, which can be used as an alternative to the above-mentioned ribs or in addition to these, the extraction air flows can be additionally performed.
  • At least one deflection device can be provided at the radially inner ends of the bleed air tubes and / or on the shaft of the gas turbine.
  • the deflection device can reduce the turbulence in the exit of the extraction air flows from the vortex rectifier in the region of the shaft and thus further reduce the pressure loss.
  • the solution of the problem in a method for guiding extraction air flows by means of the vortex rectifier, wherein the bleed air flows which flow through the hole passages in the bleed air tubes, are guided to the shaft.
  • the bleed air streams pass into first partial air streams and second partial air streams, wherein only the first partial air streams flow through the first hole passages into the bleed air tubes and the second partial air streams flow through the second hole passages into the interspaces between the bleed air tubes and are thereby guided to the shaft.
  • bleed air tubes and free hole passages directs the bleed air streams to the shaft.
  • the air undergoes a swirl reduction in the bleed air tubes, and on the other hand, the air flowing through the free hole passages also experiences a swirl reduction through the outside of the bleed air tubes.
  • the bleed air tubes thus prevent formation of a free vortex in the intermediate disc chamber.
  • the second partial air streams are additionally guided in the interstices between the bleed air tubes by means of the ribs on the bleed air tubes and / or by means of the blades. In this way, an additional swirl reduction in the partial air flow between the bleed air tubes is achieved.
  • the bleed air tubes can guide the first partial air streams and the second partial air streams in the radial direction from outside to inside. This causes a particularly low-loss flow through the vortex rectifier.
  • the bleed air tubes may carry the first partial air streams and the second partial air streams in the opposite direction to the direction of rotation of the compressor and at the same time to the shaft.
  • a fluidically favorable transition from the vortex rectifier to the shaft channel is achieved in this way.
  • the deflection device can deflect the emerging in the region of the shaft from the vortex rectifier first and second partial air flows and generate an axial total air flow from the first and second partial air streams. The flow is thus still reduced swirl, so that the turbulence at the transition from the vortex rectifier can be reduced to the wave channel.
  • the Fig. 1 and 2 show a vortex rectifier 10 according to the invention.
  • the vortex rectifier 10 comprises a carrier ring 11 with first hole passages 13, second hole passages 14 and extraction air tubes 15.
  • the ring formed as a carrier ring 11 has a flange 11 a, which is angled radially outward.
  • the first and second hole passages 13 and 14 are arranged on the periphery of the carrier ring 11.
  • a rectilinear extraction air tube 15 is arranged in each case.
  • the second hole passages 14 have no extraction air tubes 15.
  • a first hole passage 13 with a discharge air tube 15 alternates in the circumferential direction with two hole passages 14 without extraction air tubes 15. Due to this combination of first hole passages 13 with extraction air tubes 15 and second hole passages 14 without extraction air tubes 15 the vortex rectifier 10 also referred to as a combined vortex rectifier.
  • the bleed tubes 15 each have a radially outer end 15a with which the bleed air tube 15 is attached to the carrier ring 11.
  • the bleed air tubes 15 each have a radially inner end 15b which projects radially into the interior of the carrier ring 11. Between two adjacent evacuation air tubes 15 is ever a gap 16.
  • a first partial air flow 22 and a second partial air flow 23 are shown as representative of the first and second partial air flows flowing through the vortex rectifier 10.
  • the first partial air flows are caused by the entry of the in Fig. 2 Discharge air streams, not shown, into the first hole passages 13.
  • the second partial air streams are created by the entry of the in Fig. 2 Not shown, extraction air flows into the second hole passages 14.
  • the first partial air flow 22 flows radially from outside to inside through the first hole passage 13 and the discharge air tube 15 toward the shaft.
  • the second partial air flow 23 flows radially from outside to inside through the second hole passage 14 and the intermediate space 16 between two discharge air tubes 15 toward the shaft.
  • the arrow 25 indicates the direction of rotation of the compressor, not shown, and thus of the vortex rectifier 10.
  • Fig. 3 and 4 is the vortex rectifier 10 in each case in the installed position together with a first rotor disk, a second rotor disk 2 and a screw connection 12 shown.
  • the first rotor disk 1 is constructed concentrically to the center line 5 and has a radially outer region 1a, on which the screw connection 12 is located.
  • the second rotor disk 2 is also constructed concentrically to the center line 5 and has a bearing leg 4, which is of annular construction and protrudes slightly radially inwardly in the direction of the first rotor disk 1 from the radially outer region 2a of the second rotor disk 2.
  • the bearing leg 4 is provided with a radially inwardly directed flange 4a.
  • the bearing leg 4 on its circumference uniformly distributed openings 4b.
  • the flange 4 a of the bearing leg 4 is fastened by means of the screw connection 12 at the radially outer region 1 a of the first rotor disk 1.
  • the first rotor disk 1 and the second rotor disk 2 are arranged parallel to each other in the compressor, not shown, and belong to the high-pressure compressor. Between the first rotor disk 1 and the second rotor disk 2 there is an intermediate disk chamber 3 with a radially outer part 3a and a radially inner part 3b.
  • the radially outer part 3a of the intermediate disc chamber 3 is located between the carrier ring 11 of the vortex rectifier 10, the second rotor disc 2, the bearing leg 4 and the screw connection 12.
  • the radially inner part 3b of the intermediate disc chamber 3 is through the support ring 11, the first rotor disc 1 and the second rotor disc 2 limited.
  • the vortex rectifier 10 is arranged concentrically to the center line 5 and parallel to the first and second rotor disks 1 and 2.
  • the radially outwardly angled flange 11a of the carrier ring 11 of the vortex rectifier 10 is located between the radially inwardly angled flange 4a of the bearing leg 4 of the second rotor disk 2 and the outer region 1a of the first rotor disk 1 and is therefore also by means of the screw 12 at the first Rotor disc 1 attached.
  • the vortex rectifier 10 is aligned in the intermediate disc chamber 3 so that the first and second hole passages 13 and 14 radially substantially to the openings 4b in the bearing leg 4 of the second rotor disc 2 show.
  • the removal air tubes 15 can also be inserted directly into openings 4b of the bearing leg 4. In this case, no separate carrier ring 11 is required.
  • radially arranged bleed air tubes 15 can be provided in the circumferential direction opposite to the direction of rotation 25 of the compressor bleed air tubes that lead the partial air streams 22 and 23 against the direction of rotation 25 of the compressor, not shown.
  • Fig. 3 is the course of the extraction air through a first hole passage 13 and a discharge air tube 15 of the vortex rectifier 10 representative of other extraction air streams, not shown, as the first partial air flows through the first hole passages 13 and bleed air tubes 15 of the vortex rectifier 10 flow, shown.
  • the exemplified removal air flow 21 is first branched off from the compressor air flow 20 and passed through the openings 4b of the bearing leg 4 in the radially outer part 3a of the intermediate disc chamber 3. From there, a partial air flow 22 flows from the radially outer portion 3a of the intermediate disc chamber 3 through the first hole passages 13 of the vortex rectifier 10 from the radially outer end 15a of the withdrawal air tube 15 through the withdrawal air tube 15 to the radially inner end 15b of the withdrawal air tube 15.
  • Fig. 4 the course of the bleed air through a second hole passage 14 of the vortex rectifier 10 is representative of other not shown bleed air streams, which flow as second partial air streams through the second hole passages 14 of the vortex rectifier 10, shown.
  • the exemplified removal air flow 21 is first branched off from the compressor air flow 20 and passed through the openings 4b of the bearing leg 4 in the radially outer part 3a of the intermediate disc chamber 3. From there, flows a partial air flow 23 from the radially outer portion 3a of the intermediate disc chamber 3 through the second hole passages 14 and between the extraction air tubes 15, ie the partial air flow 23 flows substantially radially from outside to inside through the radially inner part 3b of the intermediate disc chamber 3 to the shaft.
  • first and second partial air flows to a total air flow 24, which continues to flow in the axial direction along a shaft, not shown.
  • the first partial air flows through the discharge air tubes 15 rectilinearly guided radially from outside to inside. As it flows through the extraction air tube 15, the partial air flow 22 cools down.
  • the extraction air tubes 15 By the extraction air tubes 15, the formation of a free vortex is prevented in the intermediate disc chamber 3 in the direction of rotation 25 of the compressor, not shown, and thus significantly reduces the pressure loss in the extraction air. At the same time, little material is required for the vortex rectifier 10.
  • the ratio of free second hole passages 14 to the first hole passages 13 connected to the extraction air tubes 15 should be as large as possible, eg 2: 1.
  • the entire vortex rectifier should have the largest possible diameter, so that the first and second partial air streams 22 and 23 are guided over as long as possible.

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

Claims (13)

  1. Réducteur de tourbillons (10) destiné à guider des flux de prélèvement d'air (21) et disposé dans une chambre entre disques (3) entre deux disques de rotor (1, 2) du compresseur d'une turbine à gaz, et comprenant au moins une couronne (11) avec des premiers passages en forme de trou (13) disposés sur sa circonférence, des seconds passages en forme de trou (14) et des tubes de prélèvement d'air (15), caractérisé en ce que seuls les premiers passages en forme de trou (13) comportent des tubes de prélèvement d'air (15), sachant que lesdits tubes de prélèvement d'air (15) sont répartis uniformément sur la circonférence de la couronne (11) et que les seconds passages en forme de trou (14) ne comportent pas de tubes de prélèvement d'air (15), et sachant que des premiers flux partiels d'air (22) peuvent être guidés à travers les premiers passages en forme de trou (13) jusqu'aux tubes de prélèvement d'air (15) et que des seconds flux partiels d'air (23) peuvent être guidés à travers les seconds passages en forme de trou (14) jusqu'aux espaces intermédiaires (16) entre les tubes de prélèvement d'air (15).
  2. Réducteur de tourbillons (10) selon la revendication n° 1, caractérisé en ce que les premiers passages en forme de trou (13) avec des tubes de prélèvement d'air (15) constituent un tiers et que les seconds passages en forme de trou (14) constituent deux tiers du nombre total de passages en forme de trou (13, 14).
  3. Réducteur de tourbillons (10) selon une des revendications n° 1 ou n° 2, caractérisé en ce que les tubes de prélèvement d'air (15) sont disposés radialement en ligne droite.
  4. Réducteur de tourbillons (10) selon une des revendications n° 1 à n° 3, caractérisé en ce que les tubes de prélèvement d'air (15) sont courbés dans la direction opposée au sens de rotation (25) du compresseur.
  5. Réducteur de tourbillons (10) selon une des revendications n° 1 à n°4, caractérisé en ce que les tubes de prélèvement d'air (15) comportent des nervures qui s'étendent dans les espaces intermédiaires (16) entre les disques de rotor (1, 2).
  6. Réducteur de tourbillons (10) selon une des revendications n° 1 à n° 5, caractérisé en ce que les tubes de prélèvement d'air (15) présentent une section ovale.
  7. Réducteur de tourbillons (10) selon une des revendications n° 1 à n° 6, caractérisé en ce qu'au moins un des deux disques de rotor (1, 2) est équipé de pales radiales qui s'étendent axialement dans les espaces intermédiaires (16) entre les tubes de prélèvement d'air (15).
  8. Réducteur de tourbillons (10) selon une des revendications n° 1 à n° 7, caractérisé en ce qu'au moins un dispositif de déviation est prévu sur les extrémités radiales intérieures (15b) des tubes de prélèvement d'air (15) et/ ou sur l'arbre de la turbine à gaz.
  9. Procédé pour guider des flux de prélèvement d'air au moyen du réducteur de tourbillons (10) selon une des revendications n° 1 à n° 8, sachant que les flux de prélèvement d'air (21) qui circulent à travers les passages en forme de trou jusqu'aux tubes de prélèvement d'air (15) sont guidés vers l'arbre, caractérisé en ce que les flux de prélèvement d'air (21) sont transformés en premiers flux partiels d'air (22) et seconds flux partiels d'air (23), sachant que seuls les premiers flux partiels d'air (22) circulent à travers les premiers passages en forme de trou (13) jusqu'aux tubes de prélèvement d'air (15) et que les seconds flux partiels d'air (23) circulent à travers les seconds passages en forme de trou (14) jusqu'aux espaces intermédiaires (16) entre les tubes de prélèvement d'air (15) et sont ainsi guidés vers l'arbre.
  10. Procédé selon la revendication n° 9, caractérisé en ce que les seconds flux partiels d'air (23) dans les espaces intermédiaires (16) entre les tubes de prélèvement d'air (15) sont de plus guidés au moyen des nervures situées sur les tubes de prélèvement d'air (15) et/ ou au moyen des pales.
  11. Procédé selon la revendication n° 9 ou n° 10, caractérisé en ce que les tubes de prélèvement d'air (15) guident les premiers flux partiels d'air (22) et les seconds flux partiels d'air (23) en direction radiale de l'extérieur vers l'intérieur.
  12. Procédé selon une des revendications n° 9 à n° 11, caractérisé en ce que les tubes de prélèvement d'air (15) guident les premiers flux partiels d'air (22) et les seconds flux partiels d'air (23) dans la direction opposée au sens de rotation (25) du compresseur et les guident en même temps vers l'arbre.
  13. Procédé selon une des revendications n° 9 à n° 12, caractérisé en ce que le dispositif de déviation dévie les premiers et seconds flux partiels d'air (22, 23) sortant du réducteur de tourbillons (10) au niveau de l'arbre, et crée ainsi à partir des premiers et seconds flux partiels d'air (22, 23) un flux d'air total (24) dans le sens axial.
EP09158557.0A 2008-05-19 2009-04-23 Redresseur de tourbillons combiné Not-in-force EP2123860B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102008024146A DE102008024146A1 (de) 2008-05-19 2008-05-19 Kombinierter Wirbelgleichrichter

Publications (3)

Publication Number Publication Date
EP2123860A2 EP2123860A2 (fr) 2009-11-25
EP2123860A3 EP2123860A3 (fr) 2015-09-02
EP2123860B1 true EP2123860B1 (fr) 2017-06-07

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Family Applications (1)

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EP09158557.0A Not-in-force EP2123860B1 (fr) 2008-05-19 2009-04-23 Redresseur de tourbillons combiné

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US (1) US8250870B2 (fr)
EP (1) EP2123860B1 (fr)
DE (1) DE102008024146A1 (fr)

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CN107023394B (zh) * 2017-04-07 2019-03-22 中国航发沈阳发动机研究所 带阻尼的管式压气机转子引气装置
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CN110173470A (zh) * 2019-05-29 2019-08-27 南京航空航天大学 一种用于航空发动机的新型复合式减涡器引气系统
CN111379736B (zh) * 2020-04-03 2021-09-03 中国航发沈阳发动机研究所 一种压气机引气结构
CN112065775A (zh) * 2020-09-15 2020-12-11 中国航发沈阳发动机研究所 一种引气导流结构及其压气机引气结构
CN114718910B (zh) * 2021-01-06 2024-09-27 中国航发商用航空发动机有限责任公司 自适应矢量减涡器、高压压气机及其引气方法
CN114790946B (zh) * 2021-01-25 2023-12-26 中国航发商用航空发动机有限责任公司 减涡器和航空发动机
CN114961893B (zh) * 2021-02-24 2023-08-04 中国航发商用航空发动机有限责任公司 航空发动机减涡器引气装置及航空发动机
CN113266599B (zh) * 2021-05-21 2022-08-09 西安交通大学 一种用于燃气轮机二次空气系统的纺锤状引气结构
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FR2491549B1 (fr) * 1980-10-08 1985-07-05 Snecma Dispositif de refroidissement d'une turbine a gaz, par prelevement d'air au niveau du compresseur
FR2614654B1 (fr) * 1987-04-29 1992-02-21 Snecma Disque de compresseur axial de turbomachine a prelevement d'air centripete
GB2207465B (en) 1987-07-18 1992-02-19 Rolls Royce Plc A compressor and air bleed arrangement
FR2672943B1 (fr) * 1991-02-20 1995-02-03 Snecma Compresseur de turbomachine equipe d'un dispositif de prelevement d'air.
US5472313A (en) * 1991-10-30 1995-12-05 General Electric Company Turbine disk cooling system
US5267832A (en) * 1992-03-30 1993-12-07 United Technologies Corporation Flarable retainer
FR2825413B1 (fr) * 2001-05-31 2003-09-05 Snecma Moteurs Dispositif de prelevement d'air par ecoulement centripete
DE10159670A1 (de) 2001-12-05 2003-06-18 Rolls Royce Deutschland Wirbelgleichrichter im Hochdruckverdichter einer Gasturbine
DE10310815A1 (de) 2003-03-12 2004-09-23 Rolls-Royce Deutschland Ltd & Co Kg Wirbelgleichrichter in Röhrenbauweise mit Haltering
DE102004006775A1 (de) * 2004-02-11 2006-10-19 Rolls-Royce Deutschland Ltd & Co Kg Wirbelgleichrichter in Röhrenbauweise
DE102004042295A1 (de) * 2004-09-01 2006-03-02 Mtu Aero Engines Gmbh Rotor für ein Triebwerk

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Publication number Publication date
EP2123860A2 (fr) 2009-11-25
EP2123860A3 (fr) 2015-09-02
US20090282834A1 (en) 2009-11-19
US8250870B2 (en) 2012-08-28
DE102008024146A1 (de) 2009-11-26

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