Gas turbine engines are described. The engines include high and low pressure turbine systems, a mid-turbine frame system arranged axially between the high and low pressure turbine systems, and a cooling air conduit fluidly connected to the mid-turbine frame system. A flow diverter assembly is installed between the cooling air conduit and the mid-turbine frame system. The flow diverter assembly includes a mounting plate to mount to the mid-turbine frame system, a manifold defining a manifold cavity on a first side of the mounting plate, a conduit connector for connecting to the cooling air conduit, and a diverter body extending from a second side of the mounting plate opposite the manifold. The diverter body has a solid base and a plurality of apertures arranged about a circumference thereof. The manifold cavity is fluidly connected to an interior of the diverter body through an aperture formed in the mounting plate.

A method of assembling a turbocharger having a vaned turbine nozzle includes first forming a sub-assembly of a center housing, shaft, bearings, compressor wheel, turbine wheel, and vane assembly. The vane assembly is held captive in attachment to the center housing by an annular heat shield that includes prongs or the like at its inner and outer peripheries for respectively engaging a first catch formed on the center housing and a second catch formed on the nozzle ring of the vane assembly. The heat shield forms a snap fit to the center housing and nozzle ring, thereby connecting the cartridge to the center housing. The whole sub-assembly is then joined to the turbine housing, in the process axially compressing the heat shield and a spring shroud for exerting an axial biasing force on the nozzle ring.

A method for controlling the clearance between the blade tips of a high-pressure turbine of a gas turbine aircraft engine and a turbine shroud, including the controlling of a valve delivering a stream of air to the turbine shroud, this method further including the following steps: the detection of a transient acceleration phase of the engine; the receiving of an item of data representative of the gas temperature at the outlet of the combustion chamber of the engine; a valve opening command, to deliver the air stream to the turbine shroud or to increase the flow rate of the delivered air stream, if the transient acceleration phase is detected and if the gas temperature at the outlet of the combustion chamber is greater than a first temperature threshold corresponding to a degraded clearance characteristic of an aged engine, this threshold being less than an operating limit temperature of the engine.

A gas turbine engine including a first turbine rotor assembly having a plurality of first turbine rotor blades extended within a gas flowpath, and a second turbine rotor assembly positioned aft along the gas flowpath of the first turbine rotor assembly. The second turbine rotor assembly is rotatably separate from the first turbine rotor assembly. A casing surrounds the first turbine rotor assembly. The casing has a unitary, integral outer casing wall extended forward of the first turbine rotor assembly and aft of the first turbine rotor assembly. The casing includes a plurality of vanes extended from the outer casing wall and through the gas flowpath aft of the first turbine rotor assembly and forward of the second turbine rotor assembly. The casing includes a plurality of walls forming thermal control rings extended outward along the radial direction from the outer casing wall. The outer casing wall and the thermal control rings is a unitary, integral structure.

Embodiments of the present invention may include a turbocharger having a turbine, a turbine housing, a variable valve, a first plate, a second plate and a heat shield member. The turbine housing accommodates the turbine and has a flow path. The variable valve rotates about each pivot member provided thereon, thereby adjusting the flow velocity of fluid guided from the flow path to the turbine. The first plate supports one end of each pivot member, and defines the flow path. The second plate supports the other end of each pivot member or the variable valves, and defines the flow path. The heat shield member covers a wall surface of the turbine housing, and defines the flow path.

Embodiments of the present invention may include a turbocharger having a turbine, a turbine housing, a variable valve, a first plate, a second plate and a heat shield member. The turbine housing accommodates the turbine and has a flow path. The variable valve rotates about each pivot member provided thereon, thereby adjusting the flow velocity of fluid guided from the flow path to the turbine. The first plate supports one end of each pivot member, and defines the flow path. The second plate supports the other end of each pivot member or the variable valves, and defines the flow path. The heat shield member covers a wall surface of the turbine housing, and defines the flow path.

An assembly for a turbine of a turbine engine, including a casing and an annular duct surrounding the casing, which can be connected to a device for supplying cooling air, and having a radially inner annular wall provided with openings arranged opposite the casing in order to cool same by the impact of cooling-air jets. The casing has a plurality of axial grooves including first grooves and second grooves arranged in alternation, and the openings are distributed in a plurality of annular rows in which any pair of consecutive annular rows is such that the openings of one of the annular rows of the pair are centered relative to the first grooves while the openings of the other annular row of the pair are centered relative to the second grooves.

An assembly for a turbine of a turbine engine, including a casing and an annular duct surrounding the casing, which can be connected to a device for supplying cooling air, and having a radially inner annular wall provided with openings arranged opposite the casing in order to cool same by the impact of cooling-air jets. The casing has a plurality of axial grooves including first grooves and second grooves arranged in alternation, and the openings are distributed in a plurality of annular rows in which any pair of consecutive annular rows is such that the openings of one of the annular rows of the pair are centered relative to the first grooves while the openings of the other annular row of the pair are centered relative to the second grooves.

Disclosed is an intake joint structure capable of blocking backflow of lubricating oil 18 at a connection position between an air inlet 12 of a turbocharger and a suction pipe 24. A backflow-preventive plate 25 is integrally molded to have a cylindrical portion 25a fitted over the air inlet 12 and a tapered portion 25b curved inward from an upstream end of the cylindrical portion 25a and converged downstream to provide an open end. A downstream end 24a of a suction pipe 24 is molded by soft material over a predetermined range using exchange blow molding. The cylindrical portion 25a of the backflow-preventive plate 25 is fitted over the air inlet 12 through a grommet 26 (first soft layer) and the downstream end 24a of the suction pipe 24 is fitted over the cylindrical portion 25a and is banded by a hose band 27.

Disclosed is an intake joint structure capable of blocking backflow of lubricating oil 18 at a connection position between an air inlet 12 of a turbocharger and a suction pipe 24. A backflow-preventive plate 25 is integrally molded to have a cylindrical portion 25a fitted over the air inlet 12 and a tapered portion 25b curved inward from an upstream end of the cylindrical portion 25a and converged downstream to provide an open end. A downstream end 24a of a suction pipe 24 is molded by soft material over a predetermined range using exchange blow molding. The cylindrical portion 25a of the backflow-preventive plate 25 is fitted over the air inlet 12 through a grommet 26 (first soft layer) and the downstream end 24a of the suction pipe 24 is fitted over the cylindrical portion 25a and is banded by a hose band 27.