A gas turbine engine includes a device for providing sealing between one rotor section and one stator section. The device includes a coating made of an abradable material attached to the stator section. The device further includes a lip on a portion of the rotor section. The lip is configured to form a seal with the abradable material. The gas turbine engine further includes passages for a gaseous fluid and means for blowing such gaseous fluid. The passages open into the rotor section provided with the lip, so that blown gaseous fluid can be present in a zone radially located between the coating and the lip.

A gas turbine engine component includes a gas turbine engine component body formed of a ceramic matrix composite material having at least one fastener integrally formed with the gas turbine engine component body as a single-piece structure. The gas turbine engine component body initially comprises a rigidized preform structure formed from a polymer based material. The at least one fastener connects the gas turbine engine component body to an engine support structure.

A gas turbine engine component includes a gas turbine engine component body formed of a ceramic matrix composite material having at least one fastener integrally formed with the gas turbine engine component body as a single-piece structure. The gas turbine engine component body initially comprises a rigidized preform structure formed from a polymer based material. The at least one fastener connects the gas turbine engine component body to an engine support structure.

In a centrifugal compressor, a diffuser channel includes a curved channel portion that bends toward a front side in an axial direction of an impeller as it goes toward an outer side in a radial direction of the impeller. In a cross-section along a rotation axis of the impeller, when a center line of the diffuser channel is A, a straight line orthogonal to the center line A at an outlet of the diffuser channel is B, and an angle between the rotation axis of the impeller and the straight line B is α, α≤60° is satisfied.

The invention relates to a method for coating a component, which is provided for the hot gas duct of a turbomachine, wherein the coating material is applied onto the uncoated component surface in the form of particles in mixture with a binding agent, and the component with the particle-treated binding agent thereupon then undergoes thermal treatment in such a way that the binding agent is released and the coating material remains on the component.

The invention relates to a method for coating a component, which is provided for the hot gas duct of a turbomachine, wherein the coating material is applied onto the uncoated component surface in the form of particles in mixture with a binding agent, and the component with the particle-treated binding agent thereupon then undergoes thermal treatment in such a way that the binding agent is released and the coating material remains on the component.

One aspect the present subject matter is directed to a nozzle segment including a stator component having an airfoil. The airfoil includes a leading edge portion, a trailing edge portion, a pressure side wall and a suction side wall and a plurality of film holes in fluid communication with the radial cooling channel. A strut is disposed within the radial cooling channel and defines an inner radial cooling passage within the radial cooling channel. The strut defines a plurality of apertures that provide for fluid communication from the inner radial cooling passage to the radial cooling channel and the plurality of film holes provide for bore cooling of the airfoil of at least one of the pressure side wall or the suction side wall and provide for film cooling of the trailing edge portion of the airfoil between about fifty percent and one hundred percent of the chord length.

A hot section of a gas turbine engine includes a stator housing wall and an at least one insulating standoff attached to the stator housing wall, extending radially away from the stator housing wall. The hot section includes an accessory module attached to an opposite end of the at least one insulating standoff away from the stator housing wall.

A hot section of a gas turbine engine includes a stator housing wall and an at least one insulating standoff attached to the stator housing wall, extending radially away from the stator housing wall. The hot section includes an accessory module attached to an opposite end of the at least one insulating standoff away from the stator housing wall.

In a method for manufacturing an article, the article has a body having: a first face; and a first bevel surface extending from the first face. A plurality of first channels along the first bevel surface extending from the first face. A ceramic coating is along the inner diameter surface and the first bevel surface. Each of the first channels are machined in the body by plunging a rotating bit into the first surface and drawing the rotating bit down the bevel surface. The coating is thereafter applied.