초록 ▼

A turbine shroud cooling system used in a gas turbine engine for controlling tip clearance between a turbine shroud assembly and turbine rotor blades comprises a cooling air passage for selectively directing a cooling air flow between components to be cooled and a turbine shroud support assembly for

A turbine shroud cooling system used in a gas turbine engine for controlling tip clearance between a turbine shroud assembly and turbine rotor blades comprises a cooling air passage for selectively directing a cooling air flow between components to be cooled and a turbine shroud support assembly for controlling the tip clearance and then later re-directing the cooling air flow to cool a downstream turbine component.

대표청구항 ▼

1. A gas turbine engine having a plurality of turbine rotor blades and a turbine shroud assembly, the turbine shroud assembly including a plurality of turbine shroud segments radially spaced apart from the plurality of turbine rotor blades, the gas turbine engine further comprising:an annular shroud

1. A gas turbine engine having a plurality of turbine rotor blades and a turbine shroud assembly, the turbine shroud assembly including a plurality of turbine shroud segments radially spaced apart from the plurality of turbine rotor blades, the gas turbine engine further comprising:an annular shroud housing adapted to be secured within a turbine support casing;turbine shroud segment attachment members mounted to an inner side of the annular shroud housing and adapted to support the turbine shroud segments in place;a first cooling air passage adapted to direct a first cooling air flow from a compressor portion of the gas turbine engine to at least one gas turbine engine component downstream of the shroud housing relative to a combustion gas path through the gas turbine engine;a second cooling air passage branching from the first cooling air passage and adapted to direct a second cooling air flow from the first cooling passage to the shroud housing to cool the shroud housing and thereby affect the tip clearance between the turbine shroud segments and the turbine rotor blades;a flow control member associated with the second cooling air passage and adapted to selectively control a cooling air flow passing through the second cooling air passage, the flow control member cooling air being selectively positionable between a first position, in which a first cooling air flow rate is permitted to pass through the second cooling air passage, and a second position, in which a second cooling air flow rate is permitted to pass through the second cooling air passage; anda third cooling air passage isolated from the second air passage, adapted to direct a third cooling air flow both for cooling the turbine shroud segment attachment members and the turbine shroud segments and for creating an air seal around the turbine shroud segments in order to prevent combustion gas leakage.2. A gas turbine engine as claimed in claim 1 wherein, the second cooling air passage is defined at least by the shroud housing, and is isolated from a section of the combustion gas path defined within the turbine shroud assembly.3. A gas turbine engine as claimed in claim 2 wherein the second cooling air passage is in fluid communication with a downstream cooling air passage of the gas turbine engine so that the cooling air flow passing to the shroud housing from the second cooling air passage is redirected therefrom to further cool a turbine component downstream of the turbine rotor blades relative to the combustion gas path.4. A gas turbine engine as claimed in claim 3 wherein the second cooling air flow rate is substantially zero.5. A gas turbine engine as claimed in claim 1 wherein the turbine shroud segment attachment members comprise a plurality of shroud support segments forming an annular ring assembly to secure the turbine shroud assembly within the shroud housing, the annular ring assembly defining said third cooling air passage.6. A gas turbine engine as claimed in claim 5 wherein the third cooling air passage is adapted to be in fluid communication with the combustion gas path defined within the turbine shroud assembly so that the third cooling air flow is adapted to be discharged into the combustion gas path after having cooled the turbine shroud assembly.7. A gas turbine engine as claimed in claim 6 wherein the first cooling air passage is adapted to be in fluid communication with an upstream cooling air passage for intake of a compressor bleed air flow, and wherein the third cooling air passage is adapted to be in fluid communication with an upstream cooling air passage for intake of full pressure compressor air to form the third cooling air flow.