A system for controlling the clearance distance between an impeller blade tip of a centrifugal compressor and a radially inner surface of an impeller shroud in a turbine engine. The system comprises a high pressure air source, an air piston mounted between an engine casing and the shroud and adapted to receive high pressure air from the high pressure air source, a mounting arm coupling the shroud and air piston, and a slidable coupling adapted to allow axial movement of the shroud and joining the shroud to an axial member.

A sealing device for suppressing a leakage flow of a fluid via an annular gap between a stationary member and a rotary member of a rotary machine includes: a fixed fin having an annular shape and disposed in the annular gap; and a movable fin having an annular shape and being disposed adjacent to the fixed fin in an axial direction inside the annular gap. The movable fin has a greater thermal expansion coefficient than the fixed fin and is fixed to the fixed fin in a fixing region on a root-end side of the movable fin.

A gas turbine having a turbine casing, an outer and inner casing part between which a hot gas flows. An annular duct is formed between the outer casing part and the turbine casing to accommodate a cooling fluid. An exhaust gas casing is positioned downstream in the flow direction of the hot gas. A bearing system for a rotor has bearing struts arranged around the circumference which extend from a shaft bearing to an outer casing and, in the hot gas path of an exhaust gas diffuser arranged in the exhaust gas casing are shielded by another strut set which surrounds the bearing struts and is hollow to support the diffuser, wherein, to center the turbine and the exhaust gas casing, these are connected to one another via a fit wherein the turbine and the exhaust gas casing can be supplied with cooling air independently of one another.

A gas turbine having a turbine casing, an outer and inner casing part between which a hot gas flows. An annular duct is formed between the outer casing part and the turbine casing to accommodate a cooling fluid. An exhaust gas casing is positioned downstream in the flow direction of the hot gas. A bearing system for a rotor has bearing struts arranged around the circumference which extend from a shaft bearing to an outer casing and, in the hot gas path of an exhaust gas diffuser arranged in the exhaust gas casing are shielded by another strut set which surrounds the bearing struts and is hollow to support the diffuser, wherein, to center the turbine and the exhaust gas casing, these are connected to one another via a fit wherein the turbine and the exhaust gas casing can be supplied with cooling air independently of one another.

An embodiment of a turbine engine outer case ring assembly includes a substantially circular first main body and a sealant layer covering at least a main gas-facing surface of the inner gas path side, the sealant layer having at least one coating sufficient to prevent infiltration of working gas into pores of the main body.

An embodiment of a turbine engine outer case ring assembly includes a substantially circular first main body and a sealant layer covering at least a main gas-facing surface of the inner gas path side, the sealant layer having at least one coating sufficient to prevent infiltration of working gas into pores of the main body.

A turbine assembly of an aircraft engine includes a cooling system for optimizing a tip clearance gap defined between an inner surface of a turbine housing and blade tips of the turbine blades. The cooling system includes a cooling airflow passage located radially outward from the turbine housing and being in heat-transfer communication with the turbine housing. The cooling airflow passage receives a flow of cooling air therethrough for cooling the turbine housing. A heat sink is disposed on the outer surface of the turbine housing within the cooling airflow passage, the heat sink including heat transfer elements projecting into the cooling airflow passage away from the outer surface of the turbine housing. The heat transfer elements are in convective heat transfer relationship with the flow of cooling air in the cooling airflow passage.

A turbine assembly of an aircraft engine includes a cooling system for optimizing a tip clearance gap defined between an inner surface of a turbine housing and blade tips of the turbine blades. The cooling system includes a cooling airflow passage located radially outward from the turbine housing and being in heat-transfer communication with the turbine housing. The cooling airflow passage receives a flow of cooling air therethrough for cooling the turbine housing. A heat sink is disposed on the outer surface of the turbine housing within the cooling airflow passage, the heat sink including heat transfer elements projecting into the cooling airflow passage away from the outer surface of the turbine housing. The heat transfer elements are in convective heat transfer relationship with the flow of cooling air in the cooling airflow passage.

The centrifugal compressor can have a shroud engaged to a case via a plurality of circumferentially interspaced slots and lugs, the slots extending in at least one of a radial direction and an axial direction relative to a rotation axis of the compressor, the lugs slidingly received in a corresponding slot and configured for sliding in the slot in response to thermal growth of the case relative to the shroud.

The centrifugal compressor can have a shroud engaged to a case via a plurality of circumferentially interspaced slots and lugs, the slots extending in at least one of a radial direction and an axial direction relative to a rotation axis of the compressor, the lugs slidingly received in a corresponding slot and configured for sliding in the slot in response to thermal growth of the case relative to the shroud.