US20080063508A1 - Fan case abradable - Google Patents

Fan case abradable Download PDF

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Publication number
US20080063508A1
US20080063508A1 US11/517,299 US51729906A US2008063508A1 US 20080063508 A1 US20080063508 A1 US 20080063508A1 US 51729906 A US51729906 A US 51729906A US 2008063508 A1 US2008063508 A1 US 2008063508A1
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US
United States
Prior art keywords
shell
recess
inlet
fan case
abradable material
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
Application number
US11/517,299
Inventor
Barry Barnett
David Denis
Andreas Eleftheriou
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.)
Pratt and Whitney Canada Corp
Original Assignee
Pratt and Whitney Canada Corp
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 Pratt and Whitney Canada Corp filed Critical Pratt and Whitney Canada Corp
Priority to US11/517,299 priority Critical patent/US20080063508A1/en
Assigned to PRATT & WHITNEY CANADA COROP reassignment PRATT & WHITNEY CANADA COROP ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: BARNETT, BARRY, ELEFTHERIOU, ANDREAS, LIU, QUANTAI
Priority to CA002600170A priority patent/CA2600170A1/en
Publication of US20080063508A1 publication Critical patent/US20080063508A1/en
Abandoned 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
    • F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan

Definitions

  • the invention relates to a fan case for a gas turbine engine having abradable material.
  • fan cases are constructed of a metal shell with abradable material encapsulated or bounded by metal surfaces within a recess machined into the metal shell surface. Since the abradable material is relatively soft and fragile, placing the abradable material in the recess between upstream and downstream walls of relatively tough and resilient metal of the shell provides protection. However, this approach is costly in time, labour, and material use, and there is room for improvement.
  • the invention provides a fan case, for a gas turbine engine, where the fan case has a hollow tubular metal shell with: a central axis of symmetry; an inlet; an outlet; and peripheral wall about the axis to encompass the tips of a plurality of rotary fan blades, and the shell wall includes an upstream portion defining an annular abradable material recess that extends axially having an upstream end at the shell inlet and a downstream end located upstream from the shell outlet.
  • the invention also provides a method of manufacturing a fan case comprising the steps of: fabricating a hollow tubular metal shell having: a central axis of symmetry; an inlet; an outlet; and peripheral wall about the axis to encompass the tips of a plurality of rotary fan blades, the shell wall including an upstream portion defining an annular abradable material recess that extends axially having an upstream end at the shell inlet and a downstream end located upstream from the shell outlet; and filling the recess with abradable material filling said recess and defining an upstream edge of unsupported abradable material radially inward of the shell inlet.
  • FIG. 1 is an axial cross-sectional view through a prior art gas turbine engine, showing the various components that are assembled to produce an engine, and an example of a prior art fan case with an encapsulated layer of abradable material.
  • FIG. 2 is a detailed axial cross-sectional view through another example of a prior art fan case with an encapsulated layer of abradable material having metal to metal contact in an upstream portion with abradable material recess downstream.
  • FIG. 4 is a detailed sectional view of the embodiment shown in FIG. 3 .
  • FIG. 5 is an exploded isometric view of the metal fan case shell bounded by front and rear flanges, and showing abradable material tiles removed from the recess in which they are bonded.
  • FIG. 6 is a like isometric view of the metal fan case shell showing abradable material tiles installed in the recess.
  • FIG. 1 shows an axial cross-section through a turbo-fan gas turbine engine. It will be understood however that the invention is equally applicable to any type of engine with a combustor and turbine section such as a turbo-shaft, a turbo-prop, or auxiliary power units.
  • Air intake into the engine passes over fan blades 1 in a fan case 2 and is then split into an outer annular flow through the bypass duct 3 and an inner flow through the low-pressure axial compressor 4 and high-pressure centrifugal compressor 5 .
  • Compressed air exits the compressor 5 through a diffuser 6 and is contained within a plenum 7 that surrounds the combustor 8 .
  • Fuel is supplied to the combustor 8 through fuel tubes 9 which is mixed with air from the plenum 7 when sprayed through nozzles into the combustor 8 as a fuel air mixture that is ignited.
  • a portion of the compressed air within the plenum 7 is admitted into the combustor 8 through orifices in the side walls to create a cooling air curtain along the combustor walls or is used for cooling to eventually mix with the hot gases from the combustor and pass over the nozzle guide vane 10 and turbines 11 before exiting the tail of the engine as exhaust.
  • the prior art fan case 2 shown in FIG. 1 has a recessed portion adjacent the tips of the fan blades 1 that includes an encapsulated layer of abradable material 12 and some designs include other impact absorbent materials such as ballistic fabric or mesh and metal honeycomb structures.
  • the recess to house the abradable material in the prior art is radially outward of the front flange 13 and the fan case 2 is bolted to the engine with the rear flange 14 . Due to the geometry of the recess, the fan case 2 is generally fabricated by machining the recess from an oversized casting and abradable material 12 is plasma spray coated into the recess.
  • FIG. 2 shows another example of a prior art fan case 2 with an enclosed layer of abradable material 12 .
  • the upstream tip of the blade 1 is in metal to metal contact with a circumferentially grooved portion of the fan case shell 15 and the blade tips contact the abradable material 12 housed in the recess downstream.
  • Metal of the fan case shell 15 axially bounds or encapsulates the relatively softer abradable material 12 upstream and downstream in this prior art example as well.
  • FIG. 3 shows an axial cross-section through the fan case 2 according to the invention with the fan case 2 being fabricated with a hollow tubular metal shell 15 having a central axis 16 of symmetry; an inlet surrounded by the front flange 13 ; an outlet surrounded by the rear flange 14 ; and peripheral metal wall 17 about the axis 16 to encompass the tips of the rotary fan blades 1 .
  • the shell wall 17 includes an upstream portion defining an annular abradable material recess 18 .
  • the recess 18 fully extends axially from it's upstream end at the shell inlet 19 surrounded by the front flange 13 to the downstream end 21 located upstream from the shell outlet 20 surrounded by the rear flange 14 .
  • the shell inlet 19 has an inlet diameter and the recess has a recess diameter that is no greater than the inlet diameter.
  • the prior art examples shown in FIGS. 1-2 show recess diameters greater than the inlet diameters and hence the abradable material is axially bounded by the metal of the fan case shell 15 in the prior art.
  • the recess diameter shown in the embodiment of FIGS. 3-4 is tapered in a downstream direction having a maximum recess diameter at the upstream end of the recess 18 that is equal to the shell inlet diameter and a minimum recess diameter at the downstream end 21 of the recess 18 .
  • the abradable material 12 partially or fully fills the recess and an upstream edge 22 of unsupported abradable material 12 radially inward of the shell inlet 19 .
  • the shell 15 includes a front flange 13 at the inlet 19 to which an inlet cowl is bolted and a rear flange 14 at the outlet 20 to bolt the fan case 2 to the engine.
  • the front flange 13 has an external diameter greater than an external diameter of the rear flange 14 as illustrated with a dashed line parallel to the axis 16 . This feature enables access to use simple metal forming techniques and reduces the need to use relatively expensive metal forging and machining methods of the prior art.
  • Fabricating the hollow tubular metal shell 15 can be accomplished with less expensive metal fabrication procedures such as: press forming sheet metal; welding; rolling sheet metal; and spin forming and need not follow the prior art methods of forging the metal shell 15 as a single oversized forging and then machining to remove excess metal material.
  • the metal fan case shell 15 may be fabricated with the forwardly open recess 18 and prefabricated molded abradable tiles 23 can slide into the recess 18 to be bonded to the metal shell 15 thereby filling the recess 18 .
  • prefabricated molded abradable tiles 23 can slide into the recess 18 to be bonded to the metal shell 15 thereby filling the recess 18 .
  • there are four tiles 23 each covering one quarter of the circumference of the recess 18 may be used.
  • the axial seam between the tiles 23 may be filled and bonded together to fill the entire recess 18 .
  • the molded abradable tiles 23 also have a molded upstream edge 22 of unsupported abradable material 12 that is disposed radially inward of the shell inlet on installation.
  • a hollow tubular metal shell 15 is fabricated having: a central axis of symmetry 16 ; an inlet 19 ; an outlet 20 ; and peripheral wall 17 about the axis 16 to encompass the tips of a plurality of rotary fan blades 1 .
  • the metal shell wall 17 includes an upstream portion defining an annular abradable material recess 18 that extends axially from the upstream end at the shell inlet 19 to the downstream end 21 located upstream from the shell outlet 20 .
  • the recess 18 is filled with abradable material 12 leaving an upstream edge 22 of unsupported abradable material 12 radially inward of the metal shell inlet 19 .
  • the step of filling the recess 18 can include molding prefabricated abradable material tiles 23 apart from the metal shell 15 and then bonding the tiles 23 into the recess 18 formed in the shell 15 .

Abstract

A fan case and method of manufacturing a fan case, for a gas turbine engine, where the fan case has a hollow tubular metal shell with: a central axis of symmetry; an inlet; an outlet; and peripheral wall about the axis to encompass the tips of a plurality of rotary fan blades, and the shell wall includes an upstream portion defining an annular abradable material recess that extends axially having an upstream end at the shell inlet and a downstream end located upstream from the shell outlet.

Description

    TECHNICAL FIELD
  • The invention relates to a fan case for a gas turbine engine having abradable material.
    • BACKGROUND OF THE ART
  • Typically, fan cases are constructed of a metal shell with abradable material encapsulated or bounded by metal surfaces within a recess machined into the metal shell surface. Since the abradable material is relatively soft and fragile, placing the abradable material in the recess between upstream and downstream walls of relatively tough and resilient metal of the shell provides protection. However, this approach is costly in time, labour, and material use, and there is room for improvement.
  • Features that distinguish the present invention from the background art will be apparent from review of the disclosure, drawings and description of the invention presented below.
    • DISCLOSURE OF THE INVENTION
  • The invention provides a fan case, for a gas turbine engine, where the fan case has a hollow tubular metal shell with: a central axis of symmetry; an inlet; an outlet; and peripheral wall about the axis to encompass the tips of a plurality of rotary fan blades, and the shell wall includes an upstream portion defining an annular abradable material recess that extends axially having an upstream end at the shell inlet and a downstream end located upstream from the shell outlet.
  • The invention also provides a method of manufacturing a fan case comprising the steps of: fabricating a hollow tubular metal shell having: a central axis of symmetry; an inlet; an outlet; and peripheral wall about the axis to encompass the tips of a plurality of rotary fan blades, the shell wall including an upstream portion defining an annular abradable material recess that extends axially having an upstream end at the shell inlet and a downstream end located upstream from the shell outlet; and filling the recess with abradable material filling said recess and defining an upstream edge of unsupported abradable material radially inward of the shell inlet.
    • DESCRIPTION OF THE DRAWINGS
  • In order that the invention may be readily understood, one embodiment of the invention is illustrated by way of example in the accompanying drawings.
  • FIG. 1 is an axial cross-sectional view through a prior art gas turbine engine, showing the various components that are assembled to produce an engine, and an example of a prior art fan case with an encapsulated layer of abradable material.
  • FIG. 2 is a detailed axial cross-sectional view through another example of a prior art fan case with an encapsulated layer of abradable material having metal to metal contact in an upstream portion with abradable material recess downstream.
  • FIG. 4 is a detailed sectional view of the embodiment shown in FIG. 3.
  • FIG. 5 is an exploded isometric view of the metal fan case shell bounded by front and rear flanges, and showing abradable material tiles removed from the recess in which they are bonded.
  • FIG. 6 is a like isometric view of the metal fan case shell showing abradable material tiles installed in the recess.
  • Further details of the invention and its advantages will be apparent from the detailed description included below.
    •  DETAILED DESCRIPTION OF PREFERRED EMBODIMENTS
  • FIG. 1 shows an axial cross-section through a turbo-fan gas turbine engine. It will be understood however that the invention is equally applicable to any type of engine with a combustor and turbine section such as a turbo-shaft, a turbo-prop, or auxiliary power units. Air intake into the engine passes over fan blades 1 in a fan case 2 and is then split into an outer annular flow through the bypass duct 3 and an inner flow through the low-pressure axial compressor 4 and high-pressure centrifugal compressor 5. Compressed air exits the compressor 5 through a diffuser 6 and is contained within a plenum 7 that surrounds the combustor 8. Fuel is supplied to the combustor 8 through fuel tubes 9 which is mixed with air from the plenum 7 when sprayed through nozzles into the combustor 8 as a fuel air mixture that is ignited. A portion of the compressed air within the plenum 7 is admitted into the combustor 8 through orifices in the side walls to create a cooling air curtain along the combustor walls or is used for cooling to eventually mix with the hot gases from the combustor and pass over the nozzle guide vane 10 and turbines 11 before exiting the tail of the engine as exhaust.
  • The prior art fan case 2 shown in FIG. 1 has a recessed portion adjacent the tips of the fan blades 1 that includes an encapsulated layer of abradable material 12 and some designs include other impact absorbent materials such as ballistic fabric or mesh and metal honeycomb structures. The recess to house the abradable material in the prior art is radially outward of the front flange 13 and the fan case 2 is bolted to the engine with the rear flange 14. Due to the geometry of the recess, the fan case 2 is generally fabricated by machining the recess from an oversized casting and abradable material 12 is plasma spray coated into the recess.
  • FIG. 2 shows another example of a prior art fan case 2 with an enclosed layer of abradable material 12. The upstream tip of the blade 1 is in metal to metal contact with a circumferentially grooved portion of the fan case shell 15 and the blade tips contact the abradable material 12 housed in the recess downstream. Metal of the fan case shell 15 axially bounds or encapsulates the relatively softer abradable material 12 upstream and downstream in this prior art example as well.
  • FIG. 3 shows an axial cross-section through the fan case 2 according to the invention with the fan case 2 being fabricated with a hollow tubular metal shell 15 having a central axis 16 of symmetry; an inlet surrounded by the front flange 13; an outlet surrounded by the rear flange 14; and peripheral metal wall 17 about the axis 16 to encompass the tips of the rotary fan blades 1.
  • As better seen in the detail of FIG. 4, the shell wall 17 includes an upstream portion defining an annular abradable material recess 18. The recess 18 fully extends axially from it's upstream end at the shell inlet 19 surrounded by the front flange 13 to the downstream end 21 located upstream from the shell outlet 20 surrounded by the rear flange 14.
  • The shell inlet 19 has an inlet diameter and the recess has a recess diameter that is no greater than the inlet diameter. Compared to the prior art examples shown in FIGS. 1-2, the prior art examples show recess diameters greater than the inlet diameters and hence the abradable material is axially bounded by the metal of the fan case shell 15 in the prior art.
  • The recess diameter shown in the embodiment of FIGS. 3-4 is tapered in a downstream direction having a maximum recess diameter at the upstream end of the recess 18 that is equal to the shell inlet diameter and a minimum recess diameter at the downstream end 21 of the recess 18. The abradable material 12 partially or fully fills the recess and an upstream edge 22 of unsupported abradable material 12 radially inward of the shell inlet 19.
  • The shell 15 includes a front flange 13 at the inlet 19 to which an inlet cowl is bolted and a rear flange 14 at the outlet 20 to bolt the fan case 2 to the engine. Of advantage in manufacturing, the front flange 13 has an external diameter greater than an external diameter of the rear flange 14 as illustrated with a dashed line parallel to the axis 16. This feature enables access to use simple metal forming techniques and reduces the need to use relatively expensive metal forging and machining methods of the prior art. Fabricating the hollow tubular metal shell 15 can be accomplished with less expensive metal fabrication procedures such as: press forming sheet metal; welding; rolling sheet metal; and spin forming and need not follow the prior art methods of forging the metal shell 15 as a single oversized forging and then machining to remove excess metal material.
  • As best seen in FIGS. 5-6 the metal fan case shell 15 may be fabricated with the forwardly open recess 18 and prefabricated molded abradable tiles 23 can slide into the recess 18 to be bonded to the metal shell 15 thereby filling the recess 18. In the embodiment illustrated there are four tiles 23 each covering one quarter of the circumference of the recess 18, however various other tile patterns can be used. The axial seam between the tiles 23 may be filled and bonded together to fill the entire recess 18. The molded abradable tiles 23 also have a molded upstream edge 22 of unsupported abradable material 12 that is disposed radially inward of the shell inlet on installation.
  • As a result of using prefabricated molded tiles 23 costs may be reduced and a greater variety of materials can be used for the abradable layer 12. Molding of the tiles 23 frees the choice of abradable materials from materials that can be powdered and plasma spray coated to materials that can be molded and then bonded to metal.
  • Although the use of a particular abradable tile is described and preferred, any suitable abradable provided in any suitable format may be used with the present method and/or apparatus.
  • Recapping the process of manufacturing a fan case 2 in accordance with the invention, the following steps are involved. A hollow tubular metal shell 15 is fabricated having: a central axis of symmetry 16; an inlet 19; an outlet 20; and peripheral wall 17 about the axis 16 to encompass the tips of a plurality of rotary fan blades 1. The metal shell wall 17 includes an upstream portion defining an annular abradable material recess 18 that extends axially from the upstream end at the shell inlet 19 to the downstream end 21 located upstream from the shell outlet 20. The recess 18 is filled with abradable material 12 leaving an upstream edge 22 of unsupported abradable material 12 radially inward of the metal shell inlet 19.
  • Since the abradable material 12 can slide into the recess 18 as shown in FIGS. 5-6, the step of filling the recess 18 can include molding prefabricated abradable material tiles 23 apart from the metal shell 15 and then bonding the tiles 23 into the recess 18 formed in the shell 15.
  • Although the above description relates to a specific preferred embodiment as presently contemplated by the inventors, it will be understood that the invention in its broad aspect includes mechanical and functional equivalents of the elements described herein.

Claims (12)

1. A fan case, for a gas turbine engine, comprising:
a hollow tubular metal shell having: a central axis of symmetry; an inlet; an outlet; and peripheral wall about the axis to encompass the tips of a plurality of rotary fan blades, wherein:
the shell wall includes an upstream portion defining an annular abradable material recess that extends axially having an upstream end at the shell inlet and a downstream end located upstream from the shell outlet.
2. A fan case according to claim 1 wherein the shell inlet has an inlet diameter and wherein the recess has a recess diameter that is no greater than the inlet diameter.
3. A fan case according to claim 2 wherein the recess diameter is tapered in a downstream direction having a maximum recess diameter at the upstream end that is equal to the inlet diameter and a minimum recess diameter at the downstream end of the recess.
4. A fan case according to claim 1 including abradable material filling said recess and defining an upstream edge of unsupported abradable material radially inward of the shell inlet.
5. A fan case according to claim 1 wherein the shell includes a front flange at the inlet and a rear flange at the outlet, and wherein the front flange has an external diameter greater than an external diameter of the rear flange.
6. A fan case according to claim 1 including molded abradable tiles bonded to the shell and filling the recess.
7. A fan case according to claim 6 wherein the molded abradable tiles have a molded upstream edge of unsupported abradable material that is disposed radially inward of the shell inlet on installation.
8. A method of manufacturing a fan case comprising the steps of:
fabricating a hollow tubular metal shell having: a central axis of symmetry; an inlet; an outlet; and peripheral wall about the axis to encompass the tips of a plurality of rotary fan blades, the shell wall including an upstream portion defining an annular abradable material recess that extends axially having an upstream end at the shell inlet and a downstream end located upstream from the shell outlet; and
filling the recess with abradable material filling said recess and defining an upstream edge of unsupported abradable material radially inward of the shell inlet.
9. A method of manufacturing according to claim 8 wherein the step of filling the recess includes:
molding prefabricated abradable material tiles apart from the shell; and
bonding said tiles to the recess in the shell.
10. A method of manufacturing according to claim 9 wherein the prefabricated abradable material tiles are molded with an upstream edge of unsupported abradable material for installation radially inward of the shell inlet.
11. A method of manufacturing according to claim 8 wherein the step of fabricating the hollow tubular metal shell consists of metal fabrication procedures selected from the group consisting of: pressing forming sheet metal; welding; rolling sheet metal; spin forming.
12. A method of manufacturing according to claim 8 wherein the step of fabricating the hollow tubular metal shell does not include forging the metal shell as a single oversized forging and then machining to remove excess metal material.
US11/517,299 2006-09-08 2006-09-08 Fan case abradable Abandoned US20080063508A1 (en)

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US11/517,299 US20080063508A1 (en) 2006-09-08 2006-09-08 Fan case abradable
CA002600170A CA2600170A1 (en) 2006-09-08 2007-09-04 Fan case abradable

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Cited By (7)

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Publication number Priority date Publication date Assignee Title
US20130343900A1 (en) * 2012-04-04 2013-12-26 Mtu Aero Engines Gmbh Process for producing a run-in coating
WO2014007875A2 (en) 2012-03-27 2014-01-09 United Technologies Corporation Gas turbine engine thrust reverser system
US8672609B2 (en) 2009-08-31 2014-03-18 United Technologies Corporation Composite fan containment case assembly
US20140294574A1 (en) * 2012-11-21 2014-10-02 Techspace Aero S.A. Stator Blades of an Axial Turbocompressor and Manufacturing Process
US9140135B2 (en) 2010-09-28 2015-09-22 United Technologies Corporation Metallic radius block for composite flange
US10876423B2 (en) 2018-12-28 2020-12-29 Honeywell International Inc. Compressor section of gas turbine engine including hybrid shroud with casing treatment and abradable section
CN114423927A (en) * 2019-09-10 2022-04-29 赛峰飞机发动机公司 Attachment of an acoustic shroud to a casing section for an aircraft turbine engine

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US6206631B1 (en) * 1999-09-07 2001-03-27 General Electric Company Turbomachine fan casing with dual-wall blade containment structure
US6702850B1 (en) * 2002-09-30 2004-03-09 Mediplex Corporation Korea Multi-coated drug-eluting stent for antithrombosis and antirestenosis
US6878531B1 (en) * 2003-11-10 2005-04-12 Medical College Of Georgia Research Institute Method for multiple site-directed mutagenesis
US20050089390A1 (en) * 2003-08-18 2005-04-28 Snecma Moteurs Abradable device on the blower casing of a gas turbine engine
US7048962B2 (en) * 2002-05-02 2006-05-23 Labcoat, Ltd. Stent coating device
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US3656862A (en) * 1970-07-02 1972-04-18 Westinghouse Electric Corp Segmented seal assembly
US4222706A (en) * 1977-08-26 1980-09-16 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Porous abradable shroud with transverse partitions
US4452335A (en) * 1982-05-03 1984-06-05 United Technologies Corporation Sound absorbing structure for a gas turbine engine
US5431532A (en) * 1994-05-20 1995-07-11 General Electric Company Blade containment system
US6113347A (en) * 1998-12-28 2000-09-05 General Electric Company Blade containment system
US6206631B1 (en) * 1999-09-07 2001-03-27 General Electric Company Turbomachine fan casing with dual-wall blade containment structure
US7048962B2 (en) * 2002-05-02 2006-05-23 Labcoat, Ltd. Stent coating device
US6702850B1 (en) * 2002-09-30 2004-03-09 Mediplex Corporation Korea Multi-coated drug-eluting stent for antithrombosis and antirestenosis
US7370467B2 (en) * 2003-07-29 2008-05-13 Pratt & Whitney Canada Corp. Turbofan case and method of making
US20050089390A1 (en) * 2003-08-18 2005-04-28 Snecma Moteurs Abradable device on the blower casing of a gas turbine engine
US6878531B1 (en) * 2003-11-10 2005-04-12 Medical College Of Georgia Research Institute Method for multiple site-directed mutagenesis

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8672609B2 (en) 2009-08-31 2014-03-18 United Technologies Corporation Composite fan containment case assembly
US9140135B2 (en) 2010-09-28 2015-09-22 United Technologies Corporation Metallic radius block for composite flange
WO2014007875A2 (en) 2012-03-27 2014-01-09 United Technologies Corporation Gas turbine engine thrust reverser system
EP2831402A4 (en) * 2012-03-27 2015-12-16 United Technologies Corp Gas turbine engine thrust reverser system
US20130343900A1 (en) * 2012-04-04 2013-12-26 Mtu Aero Engines Gmbh Process for producing a run-in coating
US9845685B2 (en) * 2012-04-04 2017-12-19 Mtu Aero Engines Gmbh Process for producing a run-in coating
US20140294574A1 (en) * 2012-11-21 2014-10-02 Techspace Aero S.A. Stator Blades of an Axial Turbocompressor and Manufacturing Process
US10876423B2 (en) 2018-12-28 2020-12-29 Honeywell International Inc. Compressor section of gas turbine engine including hybrid shroud with casing treatment and abradable section
US11421544B2 (en) 2018-12-28 2022-08-23 Honeywell International Inc. Compressor section of gas turbine engine including hybrid shroud with casing treatment and abradable section
CN114423927A (en) * 2019-09-10 2022-04-29 赛峰飞机发动机公司 Attachment of an acoustic shroud to a casing section for an aircraft turbine engine

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