Patent ID: 9134029
Filing Date: 2015-09-15
Classification: F01D,F02C,F05D,F23R

Abstract:
1. A can-annular gas turbine engine combustion arrangement, comprising: a plurality of combustor cans, each comprising a combustor inlet and a combustor outlet circumferentially and axially offset from the respective combustor inlet; an outer casing defining a plenum in which the plurality of combustor cans are disposed; and a plurality of baffles, each baffle of the plurality of baffles oriented to extend radially outward from and axially along a longitudinal axis of the gas turbine engine, and each baffle reaching the outer casing and the turbine, wherein the plurality of baffles divide the plenum into sectors, wherein each sector is bound circumferentially by two adjacent baffles and radially by the outer casing, and wherein each sector defines a respective flow path for compressed air from entry into the plenum until exiting the plenum, each baffle configured to inhibit circumferential motion of compressed air from one sector to an adjacent sector.