US 7,740,444 B2 · Methods and system for cooling integral turbine shround assemblies

Abstract

A method for cooling a turbine shroud assembly includes providing a turbine shroud assembly including a shroud segment having a leading edge, a trailing edge and a midsection defined therebetween. A shroud support circumferentially spans and supports the shroud segment. The shroud support includes a forward hanger coupled to the leading edge, a midsection hanger coupled to the midsection and an aft hanger coupled to the trailing edge. An annular shroud ring structure includes a midsection position control ring coupled to the midsection hanger and an aft position control ring coupled to the aft hanger. Cooling air is extracted from a compressor positioned upstream of the turbine shroud assembly. Cooling air is metered through the shroud support directly into only at least one active convection cooling zone defined between the shroud segment and the shroud support while substantially preventing cooling air from entering an inactive convection cooling zone positioned radially outwardly from the at least one active convection cooling zone and defined between the shroud support and the shroud ring structure and between the midsection position control ring and the aft position control ring.

Claims20

Dependent claims

A method for cooling a turbine shroud assembly, said method comprising:

providing a turbine shroud assembly comprising a shroud segment having a leading edge, a trailing edge and a midsection defined therebetween, a shroud support circumferentially spanning and supporting the shroud segment, the shroud support comprising a forward hanger coupled to the leading edge, a midsection hanger coupled to the midsection and an aft hanger coupled to the trailing edge, and an annular shroud ring structure comprising less than three position control rings, the less than three position control rings including a midsection position control ring coupled to the midsection hanger and an aft position control ring coupled to the aft hanger;
extracting cooling air from a compressor positioned upstream of the turbine shroud assembly;
and
metering cooling air through the shroud support directly into only at least one active convection cooling zone defined between the shroud segment and the shroud support.

1 more element

A turbine shroud assembly for a gas turbine engine, said turbine shroud assembly comprising:

a shroud segment comprising a leading edge, a trailing edge and a midsection defined therebetween, said shroud segment comprising a forward mounting hook at said leading edge, a midsection mounting hook at said midsection and an aft mounting hook at said trailing edge;
a shroud support circumferentially spanning and supporting said shroud segment, said shroud support comprising a forward section, a midsection and an aft section, said forward section forming a forward hanger coupled to said forward mounting hook, said midsection forming a midsection hanger coupled to said midsection mounting hook, said aft section forming an aft hanger coupled to said aft mounting hook;
an annular shroud ring structure configured to support said shroud support, said annular shroud ring structure comprising less than three position control rings, the less than three position control rings including a midsection position control ring coupled to said midsection hanger and an aft position control ring coupled to said aft hanger;
a first active convection cooling zone defined between said shroud segment and said shroud support and between said forward mounting hook and said midsection mounting hook;
at least one feed hole extending through said shroud support and configured to meter a first portion of cooling air into said first active convection cooling zone;
and
a first inactive convection cooling zone defined between said shroud support and said annular shroud ring structure and between said midsection position control ring and said aft position control ring, said shroud support substantially preventing cooling air from entering said first inactive convection cooling zone.

4 more elements

A turbine shroud cooling system for providing cooling air through a turbine shroud assembly to facilitate cooling the turbine shroud assembly, the turbine shroud assembly comprising a shroud segment having a leading edge, a trailing edge and a midsection defined therebetween, a shroud support circumferentially spanning and supporting the shroud segment, the shroud support comprising a forward hanger coupled to the leading edge, a midsection hanger coupled to the midsection and an aft hanger coupled to the trailing edge, and a shroud ring structure comprising less than three position control rings, the less than three position control rings including a midsection position control ring coupled to the midsection hanger and an aft position control ring coupled to the aft hanger, said turbine shroud cooling system configured to:

direct cooling air into a duct defined at least partially between a high pressure turbine nozzle outer band positioned upstream of the turbine shroud assembly and the shroud ring structure;
and
meter cooling air through the shroud support directly into only at least one active convection cooling zone defined between the shroud segment and the shroud support to facilitate shroud segment cooling.

Dependencies are inferred from the claim text.

Methods and system for cooling integral turbine shround assemblies

Life of this patent

Methods and system for cooling integral turbine shround assemblies

Life of this patent

Abstract

Claims20