DISTRIBUTED COOLING FOR GAS TURBINE ENGINE COMBUSTOR
First Claim
Patent Images
1. A combustor component of a gas turbine engine comprising:
- a liner panel with a refractory metal core (RMC) microcircuit which provides a self-regulating feedback.
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Abstract
A combustor component of a gas turbine engine includes a refractory metal core (RMC) microcircuit for self-regulating a cooling flow.
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Citations
20 Claims
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1. A combustor component of a gas turbine engine comprising:
a liner panel with a refractory metal core (RMC) microcircuit which provides a self-regulating feedback. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15, 16)
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17. A method of cooling a combustor of a gas turbine engine comprising:
self-regulating a cooling flow through a refractory metal core (RMC) microcircuit within a liner. - View Dependent Claims (18, 19, 20)
Specification