Patent ID: 6609362
Filing Date: 2003-08-26
Classification: F02C,F05D,F23R

Abstract:
A set of impingement cooling skins for a gas turbine engine combustor to which is attached a constituent impingement skin selected from the set of impingement cooling skins, the set of impingement skins comprising:at least a first impingement cooling skin, the first skin having a first group of holes therein adjacent to a combustor wall section defining a primary combustion zone, and a second group of holes therein adjacent to a combustor wall section defining a secondary combustion zone; and at least a second impingement cooling skin, the first second skin having a first group of holes therein adjacent to a combustor wall section defining a primary combustion zone, and a second group of holes therein adjacent to a combustor wall section defining a secondary combustion zone, wherein the number and size of the holes of the first group in each of the at least first and second cooling skins being predetermined to substantially meet a cooling requirement for the combustor; and wherein the number and size of the holes of the second group of the at least first and second cooling skins being adjusted relative to one another to substantially meet a flow distribution requirement for maintaining a substantially constant primary zone temperature when a configuration of the gas turbine engine is changed between a simple air flow cycle, when the first cooling skin is installed on the gas turbine engine, and a heat-recuperated air flow cycle, when the second cooling skin is installed on the gas turbine engine.