초록 ▼

A turbofan engine has a fan having a circumferential array of fan blades. A fan case encircles the fan. There is at least one compressor section, a combustor, and at least one turbine section. The fan case comprises a composite structural member and a metallic member encircled by the composite struc

A turbofan engine has a fan having a circumferential array of fan blades. A fan case encircles the fan. There is at least one compressor section, a combustor, and at least one turbine section. The fan case comprises a composite structural member and a metallic member encircled by the composite structural member. The metallic member is mounted to the composite structural member to permit differential thermal expansion proximate the blades.

대표청구항 ▼

1. A turbofan engine comprising: a fan having a circumferential array of fan blades;a fan case surrounding the fan;at least one compressor section;a combustor; andat least one turbine section, wherein the fan case comprises: a composite structural member;a metallic member encircled by the composite

1. A turbofan engine comprising: a fan having a circumferential array of fan blades;a fan case surrounding the fan;at least one compressor section;a combustor; andat least one turbine section, wherein the fan case comprises: a composite structural member;a metallic member encircled by the composite structural member and mounted to the composite structural member to permit differential thermal expansion proximate the blades;a plurality of radially outwardly open channels on the metallic member; anda plurality of inwardly radially projecting members received by the channels. 2. The engine of claim 1 wherein: the composite structural member comprises an organic matrix composite. 3. The engine of claim 1 further comprising: an abradable liner carried by the metallic member. 4. The engine of claim 3 wherein: the abradable liner is non-metallic; anda metallic honeycomb is radially between the abradable liner and the metallic layer. 5. The engine of claim 1 wherein at least one of: each of the radially outwardly open channels is formed by a pair of L-sectioned metallic brackets with feet oppositely circumferentially outwardly projecting and legs radially outwardly projecting;each of the inwardly radially projecting members comprises a radially-inwardly projecting portion and at least one pair of wear pads mounted circumferentially opposite each other to the radially-inwardly projecting portion and in contacting or facing relation to respective sides of the associated channel;there are 4-10 said channels;a portion of the composite structural member aft of the metallic member is secured to a mounting ring; anda portion of the composite structural member aft of the metallic member encircles and is mounted to a guide vane ring. 6. A method for operating the turbofan engine, the turbofan engine of claim 1, the method comprising: accelerating the engine from an initial condition of zero speed, a fan case initial temperature, and an initial altitude; andflying the engine to a cruise condition of a non-zero cruise speed, a fan case cruise temperature less than the fan case initial temperature, and a cruise altitude greater than the initial altitude, wherein: as the engine goes from the initial condition to the cruise condition, the differential thermal expansion radially contracts the metallic member relative to the composite structural member; andthe relative radial contraction is one or both of at least 0.3 mm or at least 0.05% of a fan tip radius at the initial condition. 7. The method of claim 6 wherein: the relative radial contraction is greater proximate a trailing extreme of the metallic member than a relative radial contraction, if any, proximate a leading extreme of the metallic member. 8. The method of claim 6 wherein: the relative radial contraction is mechanically resisted proximate a leading extreme of the metallic member. 9. A turbofan engine comprising: a fan having a circumferential array of fan blades;a fan case surrounding the fan;at least one compressor section;a combustor; andat least one turbine section, wherein: the fan case comprises: a composite structural member; anda metallic member encircled by the composite structural member and mounted to the composite structural member to permit differential thermal expansion proximate the blades; andthe metallic member is in a cartridge comprising: a first honeycomb having an ID liner encircled by a forward portion of the metallic member;a second honeycomb encircled by the metallic member aft of the first honeycomb; anda rub strip encircled by the second honeycomb. 10. The engine of claim 9 wherein: the first honeycomb comprises a metallic honeycomb;the second honeycomb comprises an aluminum alloy honeycomb with ID aluminum alloy septum; andthe rub strip comprises an epoxy-filled aramid fiber honeycomb and has ID and OD surfaces each radial converging aftward. 11. The engine of claim 9 wherein: differential thermal expansion of the metallic member is constrained at a leading extremity relative to a trailing extremity. 12. A turbofan engine fan case cartridge comprising: a metallic member;a first honeycomb having an ID liner and encircled by a forward portion of the metallic member;a second honeycomb encircled by the metallic member aft of the first honeycomb; anda rub strip encircled by the second honeycomb, wherein: the metallic member bears, along an OD surface, mounting means for engaging a fan containment case. 13. The cartridge of claim 12 wherein: the metallic member is radially stepped. 14. The cartridge of claim 13 wherein: an outboard surface of the second honeycomb is radially stepped corresponding to the radial stepping of the metallic member. 15. The cartridge of claim 12 wherein: the mounting means form channels. 16. The cartridge of claim 15 wherein: the mounting means comprise pairs of L-sectioned brackets defining said channels between legs of the brackets. 17. A method for manufacturing a turbofan engine fan case cartridge, the method comprising: assembling to a fixture, the combination of: a metallic outer member; anda liner;inserting a plurality of brackets through apertures in a sidewall of the fixture; andsecuring the brackets to the metallic outer member. 18. The method of claim 17 being a remanufacturing method re-using the metallic outer member from which a used liner has been removed. 19. The method of claim 17 further comprising: bonding the liner to the outer member. 20. The method of claim 19 wherein: the bonding comprises a vacuum bag autoclave bonding. 21. The method of claim 17 wherein: the fixture comprises a mold tool having a single axial split;the mold tool is removed from a base after the securing;the split is opened to allow removal of the assembled cartridge; andthe assembled cartridge is thereafter removed. 22. The method of claim 21 wherein: the assembling is in situ in the mold tool. 23. A fixture for manufacturing a turbofan engine fan case cartridge, the fixture comprising: a base;a mold tool having a mounted condition extending upward from the base and defining a central longitudinal axis, the mold tool comprising a sidewall with a plurality of openings; anda capture plate extending radially inward at an upper portion of the mold tool so as to define an annular axial compartment for holding the cartridge between the base and the capture plate. 24. The fixture of claim 23 wherein: the mold tool has a single split. 25. The fixture of claim 23 wherein: a plurality of members divide each of the openings into first and second circumferential portions. 26. The fixture of claim 23 wherein: an inboard surface of the mold tool is stepped. 27. The fixture of claim 23 wherein: the base is annular.