COMBUSTOR PANEL ARRANGEMENT
First Claim
1. A combustor module for a gas turbine engine, comprising:
- a first annular liner assembly extending along a longitudinal axis, the first annular liner assembly comprising a first annular support shell and a plurality of first heat shield panels coupled to the first annular support shell, the first heat shield panels forming a segmented ring defining a plurality of first axial seams therebetween;
a bulkhead coupled to the first annular liner assembly, the bulkhead providing a plurality of fuel nozzles for passing a first mass flow comprising fuel and air;
a second annular liner assembly coupled to the bulkhead, the second annular liner assembly in spaced-apart generally coaxial relationship from the first annular liner assembly by a channel height H, the second annular liner assembly comprising an air admittance hole having a mean diameter D, the air admittance hole extending along a hole axis, the hole axis being offset from the first axial seam defined by the first heat shield panels.
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Accused Products
Abstract
A combustor module for a gas turbine engine is provided that includes a first annular liner assembly extending along a longitudinal axis of the engine. The first annular liner assembly includes a first annular support shell and a plurality of first heat shield panels coupled to the first annular support shell. The first heat shield panels form a segmented ring defining a plurality of first axial seams therebetween. The combustor module further includes a bulkhead coupled to the first annular liner assembly. The bulkhead provides a plurality of fuel nozzles for passing a first mass flow comprising fuel and air. The combustor module further includes a second annular liner assembly coupled to the bulkhead. The second annular liner assembly is in spaced-apart generally coaxial relationship from the first annular liner assembly by a channel height H. The second annular liner assembly includes an air admittance hole having a mean diameter D extending along a hole axis. The hole axis is offset from the first axial seam defined by the first heat shield panels.
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Citations
21 Claims
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1. A combustor module for a gas turbine engine, comprising:
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a first annular liner assembly extending along a longitudinal axis, the first annular liner assembly comprising a first annular support shell and a plurality of first heat shield panels coupled to the first annular support shell, the first heat shield panels forming a segmented ring defining a plurality of first axial seams therebetween; a bulkhead coupled to the first annular liner assembly, the bulkhead providing a plurality of fuel nozzles for passing a first mass flow comprising fuel and air; a second annular liner assembly coupled to the bulkhead, the second annular liner assembly in spaced-apart generally coaxial relationship from the first annular liner assembly by a channel height H, the second annular liner assembly comprising an air admittance hole having a mean diameter D, the air admittance hole extending along a hole axis, the hole axis being offset from the first axial seam defined by the first heat shield panels. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10)
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11. A method for mitigating effects of maldistributed thermal loads in a combustor module, the method comprising the steps of:
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selecting a first annular liner assembly comprising a first annular support shell and a plurality of first heat shield panels coupled to the first annular support shell, the first heat shield panels forming a segmented ring defining a plurality of first axial seams therebetween; coupling a bulkhead to the first annular liner assembly; coupling a second annular liner assembly to the bulkhead, the second annular liner assembly in spaced-apart generally coaxial relationship from the first annular liner assembly by a channel height H; selecting an arrangement of air admittance holes penetrating through the second annular liner assembly, the air admittance holes having a mean diameter D and extending along a hole axis; and offsetting the air admittance holes in the second annular liner assembly from the first axial seam defined by the first heat shield panels. - View Dependent Claims (12, 13, 14, 15, 16, 17, 18, 19, 20, 21)
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Specification