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US 12,638,180 B1Granted
Combustor inlet plenum and baffle
AssigneePratt & Whitney Canada Corp.
InventorsPaul Weaver, Michel Desjardins, Guillaume Landry-Drolet
Life of this patent
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Abstract
An inlet plenum for a gas turbine engine combustor includes first and second inlet ducts fluidly connected to a distribution duct. The distribution duct extends circumferentially about an axis to fluidly connect the inlet ducts to an outlet at a radially inner boundary. The first and second inlet ducts fluidly communicate with a compressor of the gas turbine engine. A radially inner boundary of the distribution duct fluidly communicates with a combustor plenum of the gas turbine engine.
Claims20
An inlet plenum for a combustor comprising:
- a first inlet duct extending from a first inlet;
- a second inlet duct extending from a second inlet;
- and
- a distribution duct extending circumferentially about an axis and fluidly communicating with the first inlet duct at a first opening and the second inlet duct at a second opening, each of the first inlet duct, the second inlet duct, and the distribution duct located at the same axial position along the axis, and each of the first inlet duct and the second inlet duct extending in a circumferential direction about the axis and extending in a radially inward direction with respect to the axis,
- wherein the inlet plenum includes a first side and a second side separated by a fictitious plane that contains the axis, and wherein the first inlet duct is disposed on the first side and the second inlet duct is disposed on the second side, and
- wherein the first inlet duct is circumferentially spaced from the second inlet duct about the axis.
3 more elements
An inlet plenum for a combustor comprising:
- a first inlet duct extending from a first inlet;
- a second inlet duct extending from a second inlet;
- a distribution duct extending circumferentially about an axis and fluidly communicating with the first inlet duct at a first opening and the second inlet duct at a second opening, each of the first inlet duct and the second inlet duct extending in a circumferential direction about the axis and extending in a radially inward direction with respect to the axis;
- and
- a perforated plate forming a radially inner boundary of the distribution duct, wherein a plurality of apertures extends through the perforated plate
- wherein the first inlet duct, the second inlet duct, and the distribution duct are located at the same axial position coincident along the axis, and
- wherein the first inlet duct is circumferentially spaced from the second inlet duct about the axis.
4 more elements
A gas turbine engine comprising:
- a compressor;
- a combustor shell bounding an annular combustion chamber;
- a casing circumscribing the combustor shell to define a combustor plenum;
- and
- an inlet plenum fluidly connected to the combustor plenum comprising:
- a first inlet duct extending from a first inlet;
- a second inlet duct extending from a second;
- a distribution duct extending circumferentially about an axis and fluidly communicating with the first inlet at a first opening and the second inlet duct at a second opening, each of the first inlet duct, the second inlet duct, and the distribution duct located at the same axial position along the axis, and each of the first inlet duct and the second inlet duct extending in a circumferential direction about the axis and extending in a radially inward direction with respect to the axis;
- and
- a perforated plate forming a radially inner boundary of the distribution duct, wherein a plurality of apertures extends through the perforate plate;
- wherein the first inlet duct and the second inlet duct fluidly communicate with the compressor at the first inlet and the second inlet,
- wherein the radially inner boundary of the distribution duct fluidly communicates with the combustor plenum, and
- wherein the first inlet duct is circumferentially spaced from the second inlet duct about the axis.
10 more elements
Dependencies are inferred from the claim text.