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A fuel supply apparatus for an internal combustion engine includes a fuel pump disposed in a fuel tank. The fuel tank is supported by a tubular bracket secured to a mounting plate installed in an opening of a fuel tank and extending into the fuel tank. The bracket surrounds the fuel pump and restrai

A fuel supply apparatus for an internal combustion engine includes a fuel pump disposed in a fuel tank. The fuel tank is supported by a tubular bracket secured to a mounting plate installed in an opening of a fuel tank and extending into the fuel tank. The bracket surrounds the fuel pump and restrains the fuel pump along its outer periphery. The bracket may include inwardly projecting portions for restraining the fuel pump.

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A fuel supply apparatus for an internal combustion engine includes a fuel pump disposed in a fuel tank. The fuel tank is supported by a tubular bracket secured to a mounting plate installed in an opening of a fuel tank and extending into the fuel tank. The bracket surrounds the fuel pump and restrai

A fuel supply apparatus for an internal combustion engine includes a fuel pump disposed in a fuel tank. The fuel tank is supported by a tubular bracket secured to a mounting plate installed in an opening of a fuel tank and extending into the fuel tank. The bracket surrounds the fuel pump and restrains the fuel pump along its outer periphery. The bracket may include inwardly projecting portions for restraining the fuel pump. ryotechnic fluid is used to carry out the heat exchanges inside the exchanger with the derived flow of air. 14. The method of claim 13, wherein said cryotechnic fluid comprises hydrogen. 15. A method of collecting oxygen-enriched air for use in combustion in a rocket engine, comprising: separating a derived flow of air from a main flow of air through an engine during aerobic flight; separating oxygen-enriched air in said derived flow from oxygen-depleted air in said derived flow; storing said oxygen-enriched air for combustion by said rocket engine; mixing the oxygen-depleted air with said main flow; and ejecting said mixture of oxygen-depleted air and said main flow from said engine, wherein said engine comprises a turbofan engine and wherein said separation occurs upstream of the turbofan and in the turbofan of said turbofan engine. 16. A method of collecting oxygen-enriched air for use in combustion in a rocket engine, comprising: separating a derived flow of air from a main flow of air through an engine during aerobic flight; separating oxygen-enriched air in said derived flow from oxygen-depleted air in said derived flow; storing said oxygen-enriched air for combustion by said rocket engine; mixing the oxygen-depleted air with said main flow; and ejecting said mixture of oxygen-depleted air and said main flow from said engine, wherein said engine comprises a turbofan engine, and wherein said turbofan engine comprises: a high pressure spool comprising a high-pressure compressor, turbines and a combustion chamber, between said compressor and said turbines; and a low pressure spool surrounding said high pressure spool, said low pressure spool comprising a blower for collecting said main flow and said derived flow, and a low pressure turbine. 17. The method of claim 16, wherein said combustion chamber combusts a cryotechnic fluid. 18. The method of claim 17, wherein said cryotechnic fluid comprises hydrogen. 19. The method of claim 18, wherein said turbofan engine further comprises an after-burning area. 20. The method of claim 19, wherein said turbofan engine further comprises a variable-geometry nozzle. 21. The method of claim 20, wherein the flow of oxygen-depleted air passes into the after-burning area in which a flow of cryotechnic fluid is combusted before being ejected via the variable-geometry nozzle. 22. The method of claim 21, wherein the oxygen depleted air is mixed with the main flow at the outlet of the low-pressure turbine.