Kevlar wrap removal from fan casing

Abstract

Methods for removing a fiber-reinforced wrap from a fan casing are provided. The method may include heating the fiber-reinforced wrap while on a metal support (e.g., aluminum, steel, etc.) of the fan casing, unwinding a layer of the fiber-reinforced wrap from the fan casing, and winding the layer of the fiber-reinforced wrap onto a collection drum. The fiber-reinforced wrap may heated to a temperature of about 120 C. to about 200 C. (e.g., about 125 C. to about 185 C.). Systems are also generally provided for removing a fiber-reinforced wrap from a fan casing.

Claims

1. A method of removing a fiber-reinforced wrap from a fan casing, the method comprising: heating the fiber-reinforced wrap while on a metal support of the fan casing; unwinding a layer of the fiber-reinforced wrap from the fan casing; and winding the layer of the fiber-reinforced wrap onto a collection drum.

2. The method of claim 1, wherein the layer of fiber-reinforced wrap comprises polymeric fibers.

3. The method of claim 1, wherein the layer of fiber-reinforced wrap comprises fibers of poly-paraphenylene terephthalamide.

4. The method of claim 1, wherein the layer of fiber-reinforced wrap is a woven fabric.

5. The method of claim 1, wherein the fiber-reinforced wrap is heated to a temperature sufficient to soften the fiber-reinforced wrap for removal from the fan casing.

6. The method of claim 1, wherein the fiber-reinforced wrap is heated to a temperature of about 120 C. to about 200 C.

7. The method of claim 1, wherein the fiber-reinforced wrap is heated to a temperature of about 125 C. to about 185 C.

8. The method of claim 1, wherein the metal support comprises aluminum.

9. The method of claim 1, wherein the metal support comprises steel.

10. The method of claim 1, wherein the layer of fiber-reinforced wrap is passed through a tensioning roller between unwinding from the fan casing and winding onto the collection drum.

11. The method of claim 1, wherein the fiber-reinforced wrap is heated at a heated tangent line of the fan casing.

12. The method of claim 11, wherein the layer of fiber-reinforced wrap is removed from the fan casing along a release tangent line, and wherein the heated tangent line and the release tangent line are within about 60 of each other around the circumference of the fan casing.

13. The method of claim 11, wherein the layer of fiber-reinforced wrap is removed from the fan casing along a release tangent line, and wherein the heated tangent line and the release tangent line are within about 1 to about 45 of each other around the circumference of the fan casing.

14. The method of claim 1, wherein the collection drum is connected to a rolling mechanism to rotate the collection drum.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) A full and enabling disclosure of the present invention, including the best mode thereof, directed to one of ordinary skill in the art, is set forth in the specification, which makes reference to the appended Figs., in which:

(2) FIG. 1 is a schematic cross-sectional view of an exemplary gas turbine engine according to various embodiments of the present subject matter; and

(3) FIG. 2 is a perspective, cross-sectional view of an unwinding system for peeling a layer of a fiber-reinforced wrap from the fan casing and then rewinding the layer of the fiber-reinforced wrap onto a collection drum.

(4) Repeat use of reference characters in the present specification and drawings is intended to represent the same or analogous features or elements of the present invention.

DETAILED DESCRIPTION

(5) Reference now will be made in detail to embodiments of the invention, one or more examples of which are illustrated in the drawings. Each example is provided by way of explanation of the invention, not limitation of the invention. In fact, it will be apparent to those skilled in the art that various modifications and variations can be made in the present invention without departing from the scope or spirit of the invention. For instance, features illustrated or described as part of one embodiment can be used with another embodiment to yield a still further embodiment. Thus, it is intended that the present invention covers such modifications and variations as come within the scope of the appended claims and their equivalents.

(6) In the present disclosure, when a layer is being described as on or over another layer or substrate, it is to be understood that the layers can either be directly contacting each other or have another layer or feature between the layers, unless expressly stated to the contrary. Thus, these terms are simply describing the relative position of the layers to each other and do not necessarily mean on top of since the relative position above or below depends upon the orientation of the device to the viewer.

(7) As used herein, the terms first, second, and third may be used interchangeably to distinguish one component from another and are not intended to signify location or importance of the individual components.

(8) Methods are generally provided for removing a fiber-reinforced wrap from a thin metal portion of a fan casing. Generally, heat is utilized to melt the adhesive that adheres the fiber-reinforced wrap to the metal portion. Then, the fiber-reinforced wrap is removed by unwinding from the metal portion and onto a drum. As such, the metal portion of the fan casing may be reused by applying a new fiber-reinforced wrap thereon.

(9) Referring now to the drawings, FIG. 2 is a schematic cross-sectional view of an unwind system 100 in accordance with an exemplary embodiment for removing a layer 101 of a fiber-reinforced wrap 102 from a metal support 104 on the composite fan casing 18. Generally, the metal support 104 may be any suitable metal material used in composite fan casing 18, such as aluminum, an aluminum alloy, steel, etc. The fiber reinforced wrap 102 may be in the form of a fabric sheet that include polymeric fibers (e.g., fibers of poly-paraphenylene terephthalamide). In particular embodiments, the fabric sheet is a woven sheet of the polymeric fibers.

(10) The unwind system 100 is generally configured to remove the fiber-reinforced wrap 102 by unwinding the layers 101 from the metal support 104 through the use of heat. In the embodiment of FIG. 2, a heat source 106 is pointed to the heated zone 108 on the fan casing 18. In the embodiment shown, the heat source 106 focuses thermal energy locally onto a heated tangent line 109 of the fan casing 18. For example, the fiber-reinforced wrap 102 may be heated to a temperature of about 120 C. to about 200 C. at the heated tangent line 109, such as about 125 C. to about 185 C. Such temperatures may be sufficient to soften the fiber-reinforced wrap 102 for removal from the fan casing without warping or otherwise damaging the underlying metal support 104.

(11) The layer 102 is then unwound from the fan casing 18 at a release tangent line 110 just past the heated tangent line 109, such as within about 60 around the circumference of the fan casing (e.g., within about 1 to about 45). Since the release tangent line 110 is past the heated tangent line 109, the layer 101 of the fiber-reinforced wrap 102 may be more easily removed from the fan casing 18.

(12) The unwound layer 101 of fiber-reinforced wrap 102 is passed, in the shown embodiment of FIG. 2, through a tensioning roller 112 and then rewound onto a collection drum 114 so that it may be removed from the metal support 104. The tensioning roller 112 may provide sufficient force to peel the heated layer 101 from the fan casing 18 along the release tangent line 110.

(13) As stated, the system 100 may be useful for any fan casing 18 in a gas turbine engine. For example, FIG. 1 is a schematic cross-sectional view of a gas turbine engine in accordance with an exemplary embodiment of the present disclosure. More particularly, for the embodiment of FIG. 1, the gas turbine engine is a high-bypass turbofan jet engine 10, referred to herein as turbofan engine 10. Although further described below with reference to a turbofan engine 10, the present disclosure is also applicable to turbomachinery in general, including turbojet, turboprop, and turboshaft gas turbine engines, including marine and industrial turbine engines and auxiliary power units. As shown in FIG. 1, the turbofan engine 10 defines an axial direction A (extending parallel to a longitudinal centerline 12 provided for reference) and a radial direction R. In general, the turbofan 10 includes a fan section 14 and a core turbine engine 16 disposed downstream from the fan section 14.

(14) The exemplary core turbine engine 16 depicted generally includes a substantially tubular outer casing 18 that defines an annular inlet 20. The outer casing 18 encases, in serial flow relationship, a compressor section including a booster or low pressure (LP) compressor 22 and a high pressure (HP) compressor 24; a combustion section 26; a turbine section including a high pressure (HP) turbine 28 and a low pressure (LP) turbine 30; and a jet exhaust nozzle section 32. A high pressure (HP) shaft or spool 34 drivingly connects the HP turbine 28 to the HP compressor 24. A low pressure (LP) shaft or spool 36 drivingly connects the LP turbine 30 to the LP compressor 22.

(15) For the depicted embodiment, fan section 14 includes a fan 38 having a plurality of fan blades 40 coupled to a disk 42 in a spaced apart manner. As depicted, fan blades 40 extend outward from disk 42 generally along the radial direction R. The fan blades 40 and disk 42 are together rotatable about the longitudinal axis 12 by LP shaft 36. In some embodiments, a power gear box having a plurality of gears may be included for stepping down the rotational speed of the LP shaft 36 to a more efficient rotational fan speed.

(16) Referring still to the exemplary embodiment of FIG. 1, disk 42 is covered by rotatable front nacelle 48 aerodynamically contoured to promote an airflow through the plurality of fan blades 40. Additionally, the exemplary fan section 14 includes an annular fan casing or outer nacelle 50 that circumferentially surrounds the fan 38 and/or at least a portion of the core turbine engine 16. It should be appreciated that nacelle 50 may be configured to be supported relative to the core turbine engine 16 by a plurality of circumferentially-spaced outlet guide vanes 52. Moreover, a downstream section 54 of the nacelle 50 may extend over an outer portion of the core turbine engine 16 so as to define a bypass airflow passage 56 therebetween.

(17) During operation of the turbofan engine 10, a volume of air 58 enters turbofan 10 through an associated inlet 60 of the nacelle 50 and/or fan section 14. As the volume of air 58 passes across fan blades 40, a first portion of the air 58 as indicated by arrows 62 is directed or routed into the bypass airflow passage 56 and a second portion of the air 58 as indicated by arrows 64 is directed or routed into the LP compressor 22. The ratio between the first portion of air 62 and the second portion of air 64 is commonly known as a bypass ratio. The pressure of the second portion of air 64 is then increased as it is routed through the high pressure (HP) compressor 24 and into the combustion section 26, where it is mixed with fuel and burned to provide combustion gases 66.

(18) The combustion gases 66 are routed through the HP turbine 28 where a portion of thermal and/or kinetic energy from the combustion gases 66 is extracted via sequential stages of HP turbine stator vanes 68 that are coupled to the outer casing 18 and HP turbine rotor blades 70 that are coupled to the HP shaft or spool 34, thus causing the HP shaft or spool 34 to rotate, thereby supporting operation of the HP compressor 24. The combustion gases 66 are then routed through the LP turbine 30 where a second portion of thermal and kinetic energy is extracted from the combustion gases 66 via sequential stages of LP turbine stator vanes 72 that are coupled to the outer casing 18 and LP turbine rotor blades 74 that are coupled to the LP shaft or spool 36, thus causing the LP shaft or spool 36 to rotate, thereby supporting operation of the LP compressor 22 and/or rotation of the fan 38.

(19) The combustion gases 66 are subsequently routed through the jet exhaust nozzle section 32 of the core turbine engine 16 to provide propulsive thrust. Simultaneously, the pressure of the first portion of air 62 is substantially increased as the first portion of air 62 is routed through the bypass airflow passage 56 before it is exhausted from a fan nozzle exhaust section 76 of the turbofan 10, also providing propulsive thrust. The HP turbine 28, the LP turbine 30, and the jet exhaust nozzle section 32 at least partially define a hot gas path 78 for routing the combustion gases 66 through the core turbine engine 16.

(20) This written description uses examples to disclose the invention, including the best mode, and also to enable any person skilled in the art to practice the invention, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the invention is defined by the claims, and may include other examples that occur to those skilled in the art. Such other examples are intended to be within the scope of the claims if they include structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements with insubstantial differences from the literal languages of the claims.