| CPC F02C 7/224 (2013.01) [F02C 7/14 (2013.01); F02C 7/18 (2013.01); F02C 7/232 (2013.01); F02C 9/28 (2013.01); F05D 2220/323 (2013.01); F05D 2260/213 (2013.01); F05D 2270/303 (2013.01)] | 18 Claims |
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1. A method of operating a gas turbine engine, the gas turbine engine comprising:
an engine core comprising a combustor configured to burn a fuel; a turbine, the turbine comprising a plurality of turbine blades; a compressor configured to be used as a source of cooling air for the turbine blades; and an inducer configured to accelerate and direct the cooling air onto the turbine blades, the inducer comprising a plurality of airflow passageways and a modulating valve configured to control cooling air flow into a subset of the passageways; and
a fuel management system comprising two fuel-oil heat exchangers through which oil and the fuel flow, the fuel-oil heat exchangers configured to transfer heat between the oil and the fuel and comprising a primary fuel-oil heat exchanger and a secondary fuel-oil heat exchanger;
wherein the method comprises:
using the fuel management system to provide a fuel with a sulphur content of less than 30 ppm to the combustor; and
controlling the modulating valve to adjust the cooling air flow based on turbine inlet temperature, wherein
for fuel that passes through both fuel-oil heat exchangers, a ratio of heat transfer from the oil to the fuel for the primary and secondary fuel-oil heat exchangers is between 70:30 and 90:10, and
the fuel comprises sustainable aviation fuel, and the fuel is up to and including 100% sustainable aviation fuel.
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