A turbine for a turbo-machine is proposed in which, at a gas inlet for a turbine wheel, vanes extend from a nozzle ring though slots in a shroud. The nozzle ring and shroud are relatively rotatable about a rotational axis of the turbine by at least 0.1 degrees. In use, the nozzle ring and shroud are relatively rotated to bring one side of the vane into close contact with one surface of the slot, to inhibit leakage of gas between the vane and the slot surface. For this purpose the respective surfaces of the nozzle and slot can be configured to closely conform to each other. If there is differential thermal expansion of the shroud and nozzle ring, the nozzle ring and shroud can relatively rotate, to withdraw the vane from the edge of the slot to relieve the pressure between them.

The invention proposes an aeronautical turbine engine assembly comprising an upstream casing (55) to which guide blading (48a) is fastened, and a downstream casing (58) to which a sealing element (62) provided with an abradable material for rotor blading is fastened. This assembly further comprises a shroud ring (66) placed between the upstream casing and the downstream casing and fastening means (68) for detachably fastening the shroud ring. In order to be fastened to the upstream casing, the guide blading (48a) of the turbine engine is mounted on a downstream hook (480b) of the upstream casing, without being hooked onto the shroud ring (66), and the downstream casing (58) has an upstream hook with which the sealing element (62) is engaged in order to be fastened to the downstream casing, or the shroud ring has an upstream hook on which the sealing element (62) is mounted so as to be fastened to the downstream casing.

A gas turbine engine guide vane heat exchanger has guide vane heat exchanger including electroformed fluid channels in electroformed heat exchanger tubes or a heat exchanger core disposed within airfoil. Non-flammable heat conducting liquid or non-metallic foam may fill space between tubes or core and airfoil. Fluid circuit may include channels within electroformed heat exchanger tubes or the heat exchanger core and extend from inlet manifold to outlet manifold for directing fluid or oil through channels and include fluid or oil supply inlet connected to inlet manifold for receiving the fluid or oil flowed into inlet manifold and a fluid or oil supply outlet connected to fluid or oil supply outlet for discharging fluid or oil flowed out of fluid or oil outlet manifold. Heat exchanger tubes or heat exchanger core, inlet manifold, outlet manifold, supply inlet and supply outlet may be integrally and monolithically electroformed together.

Methods, apparatus, systems, and articles of manufacture to provide damping of an airfoil are disclosed. An example airfoil is disposed in a flow path, the airfoil including a shell defining an exterior surface of the airfoil and forming a cavity in an interior surface of the airfoil, and a lattice damper disposed in the cavity, the lattice damper to reduce vibrational loads exerted on the airfoil.

A nozzle assembly for a gas turbine engine includes a nozzle having a first material defining a first coefficient of thermal expansion, the nozzle having an airfoil defining a fluid passage therein, an inlet wall defining a fluid inlet that is fluidly connected to the fluid passage, and a passive valve assembly comprising an annular band, the annular band comprising a second material having a second coefficient of thermal expansion less than the first coefficient of thermal expansion such that the passive valve assembly is at least partially moveable relative to the fluid inlet.

A nozzle assembly for a gas turbine engine includes a nozzle having a first material defining a first coefficient of thermal expansion, the nozzle having an airfoil defining a fluid passage therein, an inlet wall defining a fluid inlet that is fluidly connected to the fluid passage, and a passive valve assembly comprising an annular band, the annular band comprising a second material having a second coefficient of thermal expansion less than the first coefficient of thermal expansion such that the passive valve assembly is at least partially moveable relative to the fluid inlet.

Systems and methods include providing a stator vane bushing for a variable stator vane assembly having a movable stator vane and a stator vane housing disposed annularly about the movable stator vane. The bushing includes a flange, a barrel extending from the flange, and a central aperture extending through the flange and the barrel and is disposed in the housing and annularly about the stator vane. The bushing is formed from a ceramic material having a coefficient of thermal expansion (CTE) lower than or equal to a CTE of one or more of a stator vane and a housing of the variable stator vane assembly.

A turbojet engine capable of operation in an Air Turbo Rocket (ATR) mode includes a compressor, a rotatable turbine wheel comprising turbine blades, a non-rotating guide vane ring comprising guide vanes, a turbine shaft configured to power said compressor, a combustor, a gas generator, and a main combustor. The main combustor is configured to combust hot, fuel rich gas from the gas generator in air compressed by the compressor. Hot, fuel rich gas from the gas generator is directed towards the turbine blades by a directing means.

A front centre body (FCB) structure for a geared turbofan engine comprises a plurality of vanes extending across the inlet duct to a low pressure compressor and integrates a heat exchanging arrangement to control the temperature of the gearbox of the turbofan engine.

A front centre body (FCB) structure for a geared turbofan engine comprises a plurality of vanes extending across the inlet duct to a low pressure compressor and integrates a heat exchanging arrangement to control the temperature of the gearbox of the turbofan engine.