Compact fuel-to-air heat exchanger for jet engine application

Claim 1

A compact fuel-to-air heat exchanger, in combination with a gas turbine engine having: a hot flow of cooling air; an air duct in communication with said hot flow of cooling air; a combustor section also in communication with said hot flow of cooling air and having a combustor, a combustor dome, a diffuser, and an outward combustor section casing, wherein said outward combustor section casing and said air duct define a fire safety cavity; means, disposed between said air duct and said defined fire safe cavity, for ventilating said fire safe cavity; and, a cool flow of fuel for and to said combustor; wherein said heat exchanger is disposed internal of said gas turbine engine and within said ventilated and defined fire safe cavity, and also is simultaneously disposed near said combustor dome and said diffuser, and wherein said heat exchanger comprises: a. means for cooling said hot flow of cooling air; b. means for heating said cool flow of combustor fuel, with this said means in association with said cooling air cooling means; wherein said means for cooling and said means for heating include, in common, a plurality of flow tubes through which said combustor fuel flows, with said flow tubes disposed in a crossflow relationship with and to said hot flow of cooling air, and with said fuel flow tubes having a common fuel inlet manifold and a common fuel outlet manifold; and whereby heat is transferred from said hot flow of cooling air to said cool flow of combustor fuel, thereby resulting in an exhaust flow of cooled cooling air; c. and, means for manifolding, and for directing flow of, said hot flow of cooling air and said exhaust flow of cooled cooling air, wherein said cooling air manifolding and flow-directing means includes: (1) an inlet, in said combustor section, into which said hot flow of cooling air enters; (2) means, associated with said inlet, for diverting a portion of said hot flow of entering cooling air; (3) a casing, housing said plurality of combustor fuel flow tubes; (4) a first plurality of conduits, leading from said diverting means to said casing, and connected to said diverting means and said casing, to direct said diverted portion of hot flow of cooling air to said casing, and to said plurality of combustor fuel flow tubes housed therein, whereby said diverted portion of said hot flow of cooling air is cooled; (5) a plurality of air manifolds interposed between and connected to said diverting means and said first plurality of conduits, with one air manifold for each conduit, wherein each air manifold has a plurality of intake air holes therein through which flows said diverted portion of hot flow of cooling air from said diverting means to said air manifold; (6) a second plurality of conduits, connected to and leading from said casing, to direct and to exhaust said cooled diverted portion of cooling air flow from said casing, and from said plurality of combustor fuel flow tubes housed therein, to a plurality of plenum chambers, with one plenum chamber for each conduit of said second plurality, wherein each plenum chamber is defined by a baffle and a wall of said diffuser; (7) and, a third plurality of conduits, connected to and leading from said plenum chambers through said diffuser and into a duct defined by a casing for said combustor section and a rotor drum, with said duct leading to said hot turbine and said hot turbine parts, whereby said cooled diverted portion of cooling air flow is directed from said plenum chambers to said hot turbine and hot turbine parts.