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  Fan case abradableThe Patent Description & Claims data below is from USPTO Patent Application 20080063508. Brief Patent Description - Full Patent Description - Patent Application Claims
TECHNICAL FIELD [0001]The invention relates to a fan case for a gas turbine engine having abradable material. BACKGROUND OF THE ART [0002]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. [0003]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 [0004]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. [0005]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 [0006]In order that the invention may be readily understood, one embodiment of the invention is illustrated by way of example in the accompanying drawings. [0007]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. [0008]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. [0009]FIG. 4 is a detailed sectional view of the embodiment shown in FIG. 3. [0010]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. [0011]FIG. 6 is a like isometric view of the metal fan case shell showing abradable material tiles installed in the recess. [0012]Further details of the invention and its advantages will be apparent from the detailed description included below. DETAILED DESCRIPTION OF PREFERRED EMBODIMENTS [0013]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. [0014]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. [0015]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. [0016]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. [0017]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. [0018]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. [0019]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. Continue reading... Full patent description for Fan case abradable Brief Patent Description - Full Patent Description - Patent Application Claims Click on the above for other options relating to this Fan case abradable patent application. ###  How KEYWORD MONITOR works... a FREE service from FreshPatents1. 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