US20110085897A1 - Casing comprising a peripheral shroud for a turbomachine rotor - Google Patents

Casing comprising a peripheral shroud for a turbomachine rotor Download PDF

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Publication number
US20110085897A1
US20110085897A1 US12/995,344 US99534409A US2011085897A1 US 20110085897 A1 US20110085897 A1 US 20110085897A1 US 99534409 A US99534409 A US 99534409A US 2011085897 A1 US2011085897 A1 US 2011085897A1
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United States
Prior art keywords
shroud
casing
casing according
fitting
fan
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.)
Abandoned
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US12/995,344
Inventor
Guy Bernard Vauchel
Pierre Andre Marcel Baudu
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.)
Safran Nacelles SAS
Original Assignee
Aircelle SA
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 Aircelle SA filed Critical Aircelle SA
Assigned to AIRCELLE reassignment AIRCELLE ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: BAUDU, PIERRE ANDRE MARCEL, VAUCHEL, GUY BERNARD
Publication of US20110085897A1 publication Critical patent/US20110085897A1/en
Abandoned legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • 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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the present invention concerns a casing for a turbomachine rotor, and more particularly a casing for a turbojet engine fan.
  • An airplane is moved by several turbojet engines each housed in a nacelle also housing a set of connected actuating devices related to its operation and performing various functions when the turbojet engine is in operation or stopped, such as, for example, a thrust reverser system.
  • a nacelle generally has a tubular structure comprising an air inlet upstream of the engine, a middle section designed to surround a fan of the turbojet engine, and a downstream section housing thrust reverser means and designed to surround the combustion chamber of the turbojet engine and housing thrust reverser means.
  • the fan of the turbojet engine is essentially made up of a rotary shaft carrying a plurality of vanes. At their radial ends, the blades are circumferentially surrounded by a casing.
  • the fan casings are generally machined metal elements.
  • Such an embodiment makes it possible to easily add circumferential structural reinforcing flanges on a shroud between the two ends of the casing, said flanges then being able to serve also to support engine or nacelle equipment.
  • these casings can be made of a composite material, in particular of carbon fibers.
  • the present invention aims to offset the aforementioned drawbacks, and to that end comprises a casing for a turbomachine rotor, more particularly for a turbojet engine fan, comprising a peripheral shroud designed to form a clamping collar around the casing, characterized in that the shroud has at least one fitting or flange for the attachment of equipment.
  • peripheral shroud surrounding the fan casing, the latter can be used to support the fastening elements and flanges of accessories of a nacelle or of turbojet engines intended to be fastened to said casing.
  • the casing can thus be designed from the beginning to receive determined and adapted fastening means of the shroud and will not need to be modified to directly integrate the fittings and flanges of the accessories.
  • the shroud is made from a strip that can be closed on itself.
  • the shroud is made from at least two strips that are partially peripheral and able to be joined to each other.
  • the shroud is made from two substantially half-peripheral strips.
  • the shroud is primarily metal.
  • the installation of fittings or flanges can then be done as in the prior art.
  • the shroud is made primarily of a composite material, in particular from woven composite fibers.
  • the casing comprises stops, situated on either side of the shroud so as to ensure the positioning and centering thereof, and/or stops able to prevent any rotational movement by the latter.
  • the shroud is glued on the casing.
  • the casing has, at least at the shroud, a surface having a coefficient of friction with at least part of a surface of the shroud sufficient to limit or even prevent the rotation of the shroud around the casing.
  • the casing comprises at least two shrouds each able to retain at least one base of at least one fitting, said base being introduced between the shroud and the casing.
  • the shroud is retained on the casing by at least one discrete fastening means.
  • the present invention also concerns a propulsion assembly comprising a turbojet engine housed in a nacelle, characterized in that it comprises a fan casing according to the invention.
  • FIG. 1 is a diagrammatic longitudinal cross-sectional illustration of a casing surrounding a fan of the turbojet engine.
  • FIG. 2 is an enlarged partial view in transverse cross-section of a fastening of a shroud according to the invention around the casing of FIG. 1 .
  • FIG. 3 is a diagrammatic illustration of a fitting mounted on the shroud of FIG. 2 , said fitting being oriented perpendicular to the shroud.
  • FIG. 4 is a diagrammatic illustration of a fitting mounted on the shroud of FIG. 2 , said fitting being oriented in the plane of the shroud.
  • FIG. 5 is a partial enlarged view in partial cross-section of the shroud of FIG. 2 associated with a retaining stop of the casing.
  • FIG. 6 is a partial diagrammatic view in longitudinal cross-section of a shroud arranged in a groove present in the casing.
  • FIG. 7 is a diagrammatic illustration in longitudinal cross-section of a fitting maintained on the casing using two shrouds according to the invention.
  • FIG. 8 is a partial diagrammatic illustration in longitudinal cross-section of two shrouds retained on the casing using discrete fastening means.
  • FIG. 1 shows a fan 1 of a turbojet engine 2 , said fan 1 comprising a rotary shaft 4 supporting a set of peripheral vanes 3 . At their radial ends, the vanes are circumferentially surrounded by a casing 5 ensuring the internal aerodynamic continuity of an air intake structure (not visible) and an inner wall of a downstream section (not visible) of a nacelle.
  • the casing 5 is surrounded by a peripheral shroud 6 like a clamping collar.
  • the shroud 6 illustrated in FIG. 2 is made from a strip that can be closed on itself around said casing 5 having, to that end, two ends 7 , 8 brought, in the closing position, opposite each other preferably at a longitudinal median plane of the casing 5 .
  • the shroud 6 is kept closed around the casing 5 by a screw 9 /nut 10 system.
  • a fastening system makes it possible to easily adapt the gripping of the shroud 6 on the casing 5 .
  • FIGS. 3 and 4 each show a fitting 12 , 13 supported by the shroud 6 .
  • the fitting 12 has a foot 12 a fastened in the shroud 6 using fastening means 12 b of the nut type.
  • the fitting 12 is mounted perpendicular to the shroud 6 .
  • the fitting 13 has a foot 13 a fastened in the shroud 6 using fastening means 13 b of the nut type.
  • the fitting 13 is mounted in the axis at the shroud 6 .
  • FIGS. 3 and 4 illustrate the fact that the number, size, position, orientation and shape of the fittings can vary on a same shroud 6 , and their fastening therefore does not result from the production of particular fastening means on the casing.
  • FIG. 5 shows a stop 15 situated between the ends 7 , 8 of the shroud 6 , at the closing means 9 , 10 thereof, and aims to prevent any rotation of the shroud 6 around the casing.
  • closing flanges or connecting flanges with an air intake section or a downstream section, as stop aiming to prevent the longitudinal movement of the shroud 6 .
  • these lateral stops 16 , 17 are formed by making a peripheral groove 18 in the casing 5 , the shroud 6 being positioned inside said groove 18 .
  • the peripheral groove 18 is preferably made by machining in a local overthickness of the casing 5 .
  • FIG. 7 illustrates another method of fastening a fitting 21 using two shrouds 6 .
  • the fitting 21 has a mounting foot 21 a extending on either side of said fitting 21 along a longitudinal axis of the casing 5 .
  • the foot 21 a thus has an upstream extension and a downstream extension that are each maintained by a shroud 6 on the casing 5 .
  • FIG. 8 is an example of distribution of shrouds 6 along a fan casing 5 , the shrouds 6 being fastened in the casing using discrete fastening means distributed around the casing 5 .

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The present invention relates to a casing (5) for a rotor of a turbomachine, more particularly for a fan (1) of a turbojet engine (2), comprising a peripheral shroud (6) designed to form a clamping collar around the casing, characterized in that the shroud has at least one fitting (12, 13) or flange for the attachment of equipment.

Description

    TECHNICAL FIELD
  • The present invention concerns a casing for a turbomachine rotor, and more particularly a casing for a turbojet engine fan.
    • BACKGROUND
  • An airplane is moved by several turbojet engines each housed in a nacelle also housing a set of connected actuating devices related to its operation and performing various functions when the turbojet engine is in operation or stopped, such as, for example, a thrust reverser system.
  • More precisely, a nacelle generally has a tubular structure comprising an air inlet upstream of the engine, a middle section designed to surround a fan of the turbojet engine, and a downstream section housing thrust reverser means and designed to surround the combustion chamber of the turbojet engine and housing thrust reverser means.
  • The fan of the turbojet engine is essentially made up of a rotary shaft carrying a plurality of vanes. At their radial ends, the blades are circumferentially surrounded by a casing.
  • The fan casings are generally machined metal elements.
  • Such an embodiment makes it possible to easily add circumferential structural reinforcing flanges on a shroud between the two ends of the casing, said flanges then being able to serve also to support engine or nacelle equipment.
  • For reasons related to trying to save mass, and these casings being situated in an area considered to be cold, they can be made of a composite material, in particular of carbon fibers.
  • Such an embodiment then no longer allows, or allows at prohibitive costs, integrating flanges having the same geometric configuration as for a metal casing. Generally, these components therefore cannot be used to suspend engine or nacelle equipment.
    • BRIEF SUMMARY
  • The present invention aims to offset the aforementioned drawbacks, and to that end comprises a casing for a turbomachine rotor, more particularly for a turbojet engine fan, comprising a peripheral shroud designed to form a clamping collar around the casing, characterized in that the shroud has at least one fitting or flange for the attachment of equipment.
  • Thus, by providing a peripheral shroud surrounding the fan casing, the latter can be used to support the fastening elements and flanges of accessories of a nacelle or of turbojet engines intended to be fastened to said casing.
  • The casing can thus be designed from the beginning to receive determined and adapted fastening means of the shroud and will not need to be modified to directly integrate the fittings and flanges of the accessories.
  • Moreover, in case of addition of fittings or flanges, the latter parts can easily be added on the shroud without risk of damaging the integrity of the casing by adding new fixtures.
  • It will also be noted that in case of damage or wear of the shroud, fittings or flanges, the replacement of these elements is greatly facilitated.
  • Preferably, the shroud is made from a strip that can be closed on itself.
  • Alternatively, the shroud is made from at least two strips that are partially peripheral and able to be joined to each other.
  • Advantageously, the shroud is made from two substantially half-peripheral strips.
  • Preferably, the shroud is primarily metal. The installation of fittings or flanges can then be done as in the prior art.
  • Alternatively, the shroud is made primarily of a composite material, in particular from woven composite fibers.
  • Advantageously, the casing comprises stops, situated on either side of the shroud so as to ensure the positioning and centering thereof, and/or stops able to prevent any rotational movement by the latter.
  • Preferably, the shroud is glued on the casing.
  • Also preferably, the casing has, at least at the shroud, a surface having a coefficient of friction with at least part of a surface of the shroud sufficient to limit or even prevent the rotation of the shroud around the casing.
  • According to one particular embodiment of the invention, the casing comprises at least two shrouds each able to retain at least one base of at least one fitting, said base being introduced between the shroud and the casing.
  • Advantageously, the shroud is retained on the casing by at least one discrete fastening means.
  • The present invention also concerns a propulsion assembly comprising a turbojet engine housed in a nacelle, characterized in that it comprises a fan casing according to the invention.
    • BRIEF DESCRIPTION OF THE DRAWINGS
  • The present invention will be better understood using the detailed description that follows in reference to the appended drawing, in which:
  • FIG. 1 is a diagrammatic longitudinal cross-sectional illustration of a casing surrounding a fan of the turbojet engine.
  • FIG. 2 is an enlarged partial view in transverse cross-section of a fastening of a shroud according to the invention around the casing of FIG. 1.
  • FIG. 3 is a diagrammatic illustration of a fitting mounted on the shroud of FIG. 2, said fitting being oriented perpendicular to the shroud.
  • FIG. 4 is a diagrammatic illustration of a fitting mounted on the shroud of FIG. 2, said fitting being oriented in the plane of the shroud.
  • FIG. 5 is a partial enlarged view in partial cross-section of the shroud of FIG. 2 associated with a retaining stop of the casing.
  • FIG. 6 is a partial diagrammatic view in longitudinal cross-section of a shroud arranged in a groove present in the casing.
  • FIG. 7 is a diagrammatic illustration in longitudinal cross-section of a fitting maintained on the casing using two shrouds according to the invention.
  • FIG. 8 is a partial diagrammatic illustration in longitudinal cross-section of two shrouds retained on the casing using discrete fastening means.
    •  DETAILED DESCRIPTION
  • FIG. 1 shows a fan 1 of a turbojet engine 2, said fan 1 comprising a rotary shaft 4 supporting a set of peripheral vanes 3. At their radial ends, the vanes are circumferentially surrounded by a casing 5 ensuring the internal aerodynamic continuity of an air intake structure (not visible) and an inner wall of a downstream section (not visible) of a nacelle.
  • As shown in FIG. 2, the casing 5 is surrounded by a peripheral shroud 6 like a clamping collar.
  • The shroud 6 illustrated in FIG. 2 is made from a strip that can be closed on itself around said casing 5 having, to that end, two ends 7, 8 brought, in the closing position, opposite each other preferably at a longitudinal median plane of the casing 5.
  • The shroud 6 is kept closed around the casing 5 by a screw 9/nut 10 system. Such a fastening system makes it possible to easily adapt the gripping of the shroud 6 on the casing 5.
  • FIGS. 3 and 4 each show a fitting 12, 13 supported by the shroud 6.
  • The fitting 12 has a foot 12 a fastened in the shroud 6 using fastening means 12 b of the nut type. The fitting 12 is mounted perpendicular to the shroud 6.
  • The fitting 13 has a foot 13 a fastened in the shroud 6 using fastening means 13 b of the nut type. The fitting 13 is mounted in the axis at the shroud 6.
  • FIGS. 3 and 4 illustrate the fact that the number, size, position, orientation and shape of the fittings can vary on a same shroud 6, and their fastening therefore does not result from the production of particular fastening means on the casing.
  • Indeed, a metal fan casing being a part taken up in revolution, this means that the fittings and fixtures are all in a same circumferential direction and require fittings with a complex configuration to adapt to the equipment to be supported. In the case of mounting on a shroud, the attached fittings can assume different orientations allowing a simple design, since it does not depend on the connecting area.
  • As shown in FIG. 5, the shroud 6 is kept in position using stops formed on the casing 5. In the case in point, FIG. 5 shows a stop 15 situated between the ends 7, 8 of the shroud 6, at the closing means 9, 10 thereof, and aims to prevent any rotation of the shroud 6 around the casing.
  • Any longitudinal movements of the shroud 6 along the casing 5 are also prevented by the placement of lateral stops 16, 17.
  • Of course, it is also possible to use closing flanges, or connecting flanges with an air intake section or a downstream section, as stop aiming to prevent the longitudinal movement of the shroud 6.
  • As shown in FIG. 6, these lateral stops 16, 17 are formed by making a peripheral groove 18 in the casing 5, the shroud 6 being positioned inside said groove 18. The peripheral groove 18 is preferably made by machining in a local overthickness of the casing 5.
  • FIG. 7 illustrates another method of fastening a fitting 21 using two shrouds 6.
  • In the case in point, the fitting 21 has a mounting foot 21 a extending on either side of said fitting 21 along a longitudinal axis of the casing 5. The foot 21 a thus has an upstream extension and a downstream extension that are each maintained by a shroud 6 on the casing 5.
  • FIG. 8 is an example of distribution of shrouds 6 along a fan casing 5, the shrouds 6 being fastened in the casing using discrete fastening means distributed around the casing 5.
  • Although the invention has been described with specific embodiments, it is obviously in no way limited thereto and encompasses all technical equivalents of the means described as well as combinations thereof if they are within the scope of the invention.

Claims (12)

1. A casing for a turbomachine rotor, more particularly for a turbojet engine fan, comprising a peripheral shroud designed to form a clamping collar around the casing, wherein the shroud has at least one fitting or a flange for the attachment of equipment.
2. The casing according to claim 1, wherein the shroud is made from a strip that can be closed on itself.
3. The casing according to claim 1, wherein the shroud is made from at least two partially peripheral strips that are able to be joined to each other.
4. The casing according to claim 3, wherein the shroud is made from two substantially half-peripheral strips.
5. The casing according to claim 1, wherein the shroud is primarily metal.
6. The casing according to claim 1, wherein the shroud is primarily made of a composite material in particular from woven composite fibers.
7. The casing according to claim 1, further comprising stops situated on either side of the shroud so as to ensure positioning and centering thereof and/or stops able to prevent any rotational movement of the latter part.
8. The casing according to claim 1, wherein the shroud is glued on the casing.
9. The casing according to claim 1, further comprising, at least at the shroud, a surface having a coefficient of friction with at least part of a surface of the shroud sufficient to limit or even prevent the rotation of the shroud around the casing.
10. The casing according to claim 1, further comprising at least two shrouds capable of each retaining at least one base of at least one fitting, said base being introduced between the shroud and the casing.
11. The casing according to claim 1, wherein the shroud is retained on the casing by at least one discrete fastening means.
12. A propulsion assembly comprising a turbojet engine housed in a nacelle, wherein it comprises a fan casing according to claim 1.
US12/995,344 2008-06-06 2009-03-30 Casing comprising a peripheral shroud for a turbomachine rotor Abandoned US20110085897A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR0803156A FR2932233B1 (en) 2008-06-06 2008-06-06 CARTER FOR ROTOR OF TURBOMACHINE
FR08/03156 2008-06-06
PCT/FR2009/000366 WO2009147307A1 (en) 2008-06-06 2009-03-30 Casing comprising a peripheral shroud for a turbomachine rotor

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US20110085897A1 true US20110085897A1 (en) 2011-04-14

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US12/995,344 Abandoned US20110085897A1 (en) 2008-06-06 2009-03-30 Casing comprising a peripheral shroud for a turbomachine rotor

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US (1) US20110085897A1 (en)
EP (1) EP2288798A1 (en)
CN (1) CN102016265B (en)
BR (1) BRPI0912082A2 (en)
CA (1) CA2726024A1 (en)
FR (1) FR2932233B1 (en)
RU (1) RU2511960C2 (en)
WO (1) WO2009147307A1 (en)

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EP2789827A4 (en) * 2011-12-07 2015-03-18 Ihi Corp Installation boss and fan case
US9017021B2 (en) 2010-10-22 2015-04-28 Snecma Aeroengine fan casing made of composite material, and a method of fabricating it
EP3026247B1 (en) * 2014-11-26 2020-12-30 United Technologies Corporation Composite fan housing assembly of a turbofan engine and method of manufacture

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FR2963469B1 (en) * 2010-07-27 2012-07-27 Aircelle Sa ACOUSTIC PANEL
EP2733314B1 (en) * 2012-11-15 2017-04-05 Safran Aero Boosters SA Radial attachment and positioning flanges for axial turbomachine casing sections
FR3058343B1 (en) * 2016-11-04 2020-02-28 Safran Aircraft Engines IMPROVED MACHINING SYSTEM FOR A FLANGE FOR FIXING AN AIRCRAFT TURBOMACHINE HOUSING
FR3074855A1 (en) * 2017-12-11 2019-06-14 Airbus Operations GRID FOR FORMATION OF AN INVERSION FLOW OF AN AIRCRAFT TURBOJET ENGINE
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BRPI0912082A2 (en) 2015-10-06
EP2288798A1 (en) 2011-03-02
CN102016265B (en) 2014-06-18
CA2726024A1 (en) 2009-12-10
WO2009147307A1 (en) 2009-12-10
FR2932233A1 (en) 2009-12-11
FR2932233B1 (en) 2012-09-28
CN102016265A (en) 2011-04-13
RU2511960C2 (en) 2014-04-10
RU2010152292A (en) 2012-07-20

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