Patent ID: 9657642
Date: 2017-05-23
CPC Classifications: F01D,F02C,F05D,Y02T

Claim:
1. A turbine section of a gas turbine engine, comprising: a stator assembly comprising an inner diameter end wall, an outer diameter end wall, and a stator vane extending between the inner diameter end wall and the outer diameter end wall within a mainstream gas flow path; a turbine rotor assembly downstream of the stator assembly and including a rotor blade extending into the mainstream gas flow path; a housing including an annular shroud that circumscribes the rotor blade and at least partially defines the mainstream hot gas flow path; a first baffle arranged to define a first cavity with the outer diameter end wall of the stator assembly; a second baffle; and a third baffle arranged to define a second cavity with the second baffle and a third cavity with the shroud, wherein the first cavity is fluidly coupled to the second cavity and the second cavity is fluidly coupled to the third cavity such that cooling air flows from the first cavity to the second cavity and from the second cavity to the third cavity, wherein the first baffle includes a first set of holes configured to direct a first portion of cooling air to impinge on the outer diameter end wall, wherein the stator assembly includes an aft rail extending radially from the outer diameter end wall to the first baffle, and wherein the aft rail defines a second set of cooling holes to fluidly couple the first cavity to the second cavity, wherein the first baffle is configured to direct the first portion of cooling air to impinge on an aft end of the outer diameter end wall, wherein the first cavity is formed by a first sub-cavity proximate to a leading edge of the outer diameter end wall, a second sub-cavity proximate to the stator vane, and a third sub-cavity proximate to the aft end of the outer diameter end wall, wherein the first, second, and third sub-cavities are fluidly isolated from one another.