Methods and apparatus for cooling gas turbine engines
First Claim
1. A method for assembling a gas turbine engine assembly, said method comprising:
- mounting a gas turbine engine including an inlet and an exhaust within a module that includes an inlet area, an exhaust area, and an engine area extending therebetween, such that the gas turbine engine is housed within the module;
coupling a first deflector within the module engine area such that when cooling air is channeled past the deflector, the deflector induces a substantially helically-shaped cooling air flowpath around a periphery of the gas turbine engine; and
coupling an exhaust duct to an outlet of the module exhaust area.
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Abstract
A method for assembling a gas turbine engine assembly that includes mounting a gas turbine engine including an inlet and an exhaust within a module that includes an inlet area, an exhaust area, and an engine area extending therebetween, such that the gas turbine engine is housed within the module, coupling a first deflector within the module engine area such that when cooling air is channeled past the deflector, the deflector induces a substantially helically-shaped cooling air flowpath around a periphery of the gas turbine engine, and coupling an exhaust duct to an outlet of the module exhaust area.
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Citations
20 Claims
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1. A method for assembling a gas turbine engine assembly, said method comprising:
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mounting a gas turbine engine including an inlet and an exhaust within a module that includes an inlet area, an exhaust area, and an engine area extending therebetween, such that the gas turbine engine is housed within the module;
coupling a first deflector within the module engine area such that when cooling air is channeled past the deflector, the deflector induces a substantially helically-shaped cooling air flowpath around a periphery of the gas turbine engine; and
coupling an exhaust duct to an outlet of the module exhaust area. - View Dependent Claims (2, 3, 4, 5)
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6. A cooling system for a gas turbine engine assembly including a module and a gas turbine engine housed within said module, said cooling system comprising:
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a first deflector coupled within said module; and
a first supply fan configured to channel cooling air through said first deflector such that a substantially helically-shaped cooling air flowpath is generated around said gas turbine engine. - View Dependent Claims (7, 8, 9, 10, 11, 12, 13)
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14. A gas turbine engine assembly comprising:
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a module;
a gas turbine engine housed within said module; and
a cooling system for cooling said gas turbine engine comprising;
a first deflector coupled within said module; and
a first supply fan configured to channel cooling air through said first deflector such that a substantially helically-shaped cooling air flowpath is generated around said gas turbine engine. - View Dependent Claims (15, 16, 17, 18, 19, 20)
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Specification