MECHANICAL JOINT FOR A GAS TURBINE ENGINE
First Claim
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1. A mechanical joint for a gas turbine engine, comprising:
- (a) an annular first component having an annular, radially-extending first flange;
(b) an annular second component having an annular, radially-extending second flange abutting the first flange;
(c) a plurality of generally radially-extending radial channels passing through at least one of the first and second flanges;
(d) a plurality of generally axially-extending channels extending through the first flange and communicating with respective ones of the radial channels; and
(e) a plurality of fasteners clamping the first and second flanges together.
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Abstract
A mechanical joint for a gas turbine engine includes:(a) an annular first component having an annular, radially-extending first flange; (b) an annular second component having an annular, radially-extending second flange abutting the first flange; (c) a plurality of generally radially-extending radial channels passing through at least one of the first and second flanges; (d) a plurality of generally axially-extending channels extending through the first flange and communicating with respective ones of the radial channels; and (e) a plurality of fasteners clamping the first and second flanges together.
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Citations
20 Claims
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1. A mechanical joint for a gas turbine engine, comprising:
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(a) an annular first component having an annular, radially-extending first flange; (b) an annular second component having an annular, radially-extending second flange abutting the first flange; (c) a plurality of generally radially-extending radial channels passing through at least one of the first and second flanges; (d) a plurality of generally axially-extending channels extending through the first flange and communicating with respective ones of the radial channels; and (e) a plurality of fasteners clamping the first and second flanges together. - View Dependent Claims (2, 3, 4, 17, 18)
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5. A joint structure for a gas turbine engine, comprising:
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(a) an annular nozzle support coupled to a stationary turbine nozzle, including a radially-extending nozzle support flange, the nozzle support flange having a plurality of generally radially-extending first grooves formed therein; (b) an annular diffuser including a plurality of streamlined struts and a diffuser arm carrying a radially-extending diffuser flange abutting the nozzle support flange, the diffuser flange including a plurality of generally radially-extending second grooves formed therein, wherein the first and second grooves are circumferentially aligned so as to cooperatively define radial channels; (c) an annular outlet guide vane structure including a plurality of airfoil-shaped vanes and an outlet guide vane arm carrying a radially-extending outlet guide vane flange which abuts the diffuser flange, wherein the diffuser arm and the outlet guide vane arm cooperatively define an open volume therebetween; (d) a plurality of generally axially-extending channels extending through the diffuser and outlet guide flanges, and communicating with respective ones of the radial channels and the open volume; and (e) a plurality of fasteners clamping the nozzle support flange, diffuser flange, and outlet guide vane flange together. - View Dependent Claims (6, 7, 8, 9, 10, 11, 12, 13, 14, 19, 20)
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- 15. A method of reducing thermal gradients in a mechanical joint for a gas turbine engine of the type including two or more annular components each having radially-extending flanges which are clamped together with a plurality of fasteners, wherein exterior surfaces of the annular components are exposed in operation to high-temperature gases, the method comprising passing high-temperature gases from the exterior through central portions of the clamped flanges.
Specification