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A turbine section includes a stator assembly having an inner diameter end wall, an outer diameter end wall, and a stator vane; a turbine rotor assembly including a rotor blade extending into the mainstream gas flow path; a housing including an annular shroud that circumscribes the rotor blade and at

A turbine section includes a stator assembly having an inner diameter end wall, an outer diameter end wall, and a stator vane; a turbine rotor assembly 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. 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.

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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 do

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; anda 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, andwherein 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. 2. The turbine section of claim 1, wherein the rotor blade has a leading edge and a trailing edge, and wherein the third baffle extends in an axial direction between the leading edge and the trailing edge of the rotor blade. 3. The turbine section of claim 1, wherein the third baffle includes a third set of holes configured to direct the first portion of cooling air into the third cavity to impinge on the shroud. 4. The turbine section of claim 3, wherein the third set of holes is configured to direct the first portion of cooling air into the third cavity and onto a radially outer surface of the shroud. 5. The turbine section of claim 4, further comprising a fourth baffle within the second cavity. 6. The turbine section of claim 4, further comprising a main cavity supplying the cooling air to the first cavity, and wherein the second baffle forms a seal to block the cooling air from flowing directly from the main cavity into the second cavity. 7. A method for cooling turbine components in a gas turbine engine, comprising the steps of: directing a flow of cooling air from a main cavity through a first set of holes in a first baffle into a first cavity to impinge on an outer diameter end wall of a stator assembly;directing a first portion of the flow of cooling air through a second set of holes in an aft rail of the outer diameter end wall of the stator assembly radially outward into a second cavity; anddirecting the first portion of the flow of cooling air through a third set of holes in a second baffle into a third cavity to impinge onto a radially outer surface of a rotor shroud,wherein the second cavity is formed by a third baffle and the second baffle, and wherein the method further comprises sealing the third baffle and the first baffle to block the flow of cooling air from flowing directly from the main cavity into the second cavity, andwherein 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, and wherein the step of directing the flow of cooling air from the main cavity through the first set of holes includes fluidly isolating the first, second, and third sub-cavities from one another. 8. The method of claim 7, wherein the step of directing the flow of cooling air from the main cavity through the first set of holes in the first baffle into the first cavity includes directing the flow of cooling air at an angle of 90° to impinge on the outer diameter end wall of the stator assembly. 9. The method of claim 8, wherein the step of directing the first portion of the flow of cooling air through the third set of holes in the second baffle into the third cavity includes directing the first portion of the flow of cooling air at an angle of 90° to impinge on the rotor shroud.