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An apparatus for supplying inlet gas 29 and fuel 17 to a gas turbine engine 10, the apparatus comprising: a heat exchanger 28 for transferring thermal energy from the inlet gas 29 to a fuel 17 for the gas turbine engine 10, the heat exchanger 28 comprising a first input for receiving fuel 17, a seco

An apparatus for supplying inlet gas 29 and fuel 17 to a gas turbine engine 10, the apparatus comprising: a heat exchanger 28 for transferring thermal energy from the inlet gas 29 to a fuel 17 for the gas turbine engine 10, the heat exchanger 28 comprising a first input for receiving fuel 17, a second input for receiving inlet gas 29, a first output for providing inlet gas 31 after heat exchange to the gas turbine engine 10 and a second output for providing fuel 33 after heat exchange to the gas turbine engine 10.

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We claim: 1. A gas turbine engine comprising a compressor, a combustor, a turbine and an apparatus for supplying inlet gas to the compressor of the gas turbine engine and fuel to the combustor of the gas turbine engine, the apparatus comprising a first heat exchanger, a second heat exchanger and co

We claim: 1. A gas turbine engine comprising a compressor, a combustor, a turbine and an apparatus for supplying inlet gas to the compressor of the gas turbine engine and fuel to the combustor of the gas turbine engine, the apparatus comprising a first heat exchanger, a second heat exchanger and cooling means, the cooling means receiving gas bled from the compressor of the gas turbine engine, the cooling means reducing the thermal energy of the gas, the first heat exchanger comprising a first input for receiving the gas from the cooling means and a second input for receiving a fuel, the first heat exchanger transferring thermal energy from the fuel to the gas, the second heat exchanger comprising a first input for receiving inlet gas from the compressor, the second heat exchanger transferring thermal energy from the inlet gas to the fuel, a first output of the second heat exchanger providing inlet gas to the compressor of the gas turbine engine and a second output of the second heat exchanger providing fuel to the combustor of the gas turbine engine. 2. A gas turbine engine as claimed in claim 1, further comprising a pump for pumping the fuel to a pressure level above a threshold value for entering the gas turbine engine. 3. A gas turbine engine as claimed in claim 1, wherein the cooling means comprises a further heat exchanger, wherein the further heat exchanger comprises a first input for receiving gas bled from the compressor of the gas turbine engine, a second input for receiving fuel from the first heat exchanger, a first output for providing fuel to the first input of the second heat exchanger, a second output for providing gas to the cooling means, the further heat exchanger transfers thermal energy from the gas bled from the compressor to the fuel. 4. A gas turbine engine as claimed in claim 3, wherein the fuel provided to the further heat exchanger is a liquefied fuel. 5. A gas turbine engine as claimed in claim 4, wherein the pump provides liquefied fuel to the further heat exchanger. 6. A gas turbine engine as claimed in claim 4, wherein the liquefied fuel is vaporised by the further heat exchanger. 7. A gas turbine engine as claimed in claim 1, wherein the cooling means is a turbine. 8. A gas turbine engine as claimed in claim 7, wherein the turbine is a turbine of the gas turbine engine or an external turbine. 9. A gas turbine engine as claimed in claim 1, wherein the cooling means is electrically connected to a load and supplies electrical energy to the load. 10. A method of supplying inlet gas to the compressor of a gas turbine engine and fuel to the combustor of a gas turbine engine, the method comprising bleeding gas from the compressor of the gas turbine engine, cooling the gas bled from the compressor of the gas turbine engine to provide cooled gas, transferring thermal energy from a fuel to the cooled gas in a first heat exchanger to provide cooled fuel, transferring thermal energy from the inlet gas to the cooled fuel in a second heat exchanger, providing the cooled inlet gas to the compressor of the gas turbine engine and providing said fuel to the combustor of the gas turbine engine. 11. A method as claimed in claim 10 comprising cooling the gas bled from the compressor in a turbine. 12. A method as claimed in claim 11 comprising cooling the gas bled from the compressor by transferring thermal energy from the gas bled from the compressor to the fuel in a further heat exchanger supplying the gas to the turbine and supplying the fuel to the second heat exchanger. 13. A method as claimed in claim 12 wherein the first heat exchanger provides liquefied fuel. 14. A method as claimed in claim 13 wherein the further heat exchanger provides vaporized fuel.