A gas turbine engine defining an axial direction and a radial direction, and including a primary cooling circuit configured to receive a first flow of air; and a turbine rotor comprising a rotor blade, the rotor blade defining at least in part a forward wheelspace that is located forward of the rotor blade, the forward wheelspace configured to receive a second flow of air, the rotor blade further defining: a first cooling circuit internal to the rotor blade and in fluid communication with the primary cooling circuit for receiving the first flow of air from the primary cooling circuit; a second cooling circuit internal to the rotor blade and in fluid communication with the forward wheelspace for receiving a portion of the second flow of air from the forward wheelspace; and a means for drawing a portion of the second flow of air into the second cooling circuit.

The combustor for a rocket engine includes a combustion room configured to cause a combustion reaction between a fuel and an oxidant, an injector configured to inject the fuel and the oxidant into the combustion room, and a nozzle skirt configured to inject combustion gas generated by the combustion reaction to an outside, and an inertance increasing portion configured to increase an equivalent inertance in a vibration equivalent circuit of the combustor for the rocket engine.

A turbofan gas turbine engine configured to reduce hotspots within combustors. The engine includes an axis and a combustor that is circumferentially disposed about the axis. The combustor includes an annular combustor liner that includes a front portion and a rear portion. The annular combustor liner is joined to an annular combustor dome via front portion and defines a chamber and a nozzle is mounted within the annular combustor dome and is configured to inject fuel into a plurality of swirlers. At least one or more dilution openings is circumferentially distributed around the liner such that a region is fluidly connected through the annular combustor liner to the chamber. Each one of the pluralities of dilution openings includes an opening and a radial support wall that is positioned aft of the opening such that the radial support wall extends into the chamber.

An impingement insert for an airfoil of a turbomachine component is provided. The insert includes first and second body parts, each having inner and outer surfaces; and first and second contact parts provided on the outer surfaces of the first and the second body parts. The insert includes a flexible mechanical seal part between the body parts. A flow channel for cooling air is defined by the seal part and the inner surfaces of the body parts. One or both of the body parts include impingement holes. The insert has an elastic part connected to the body parts. When the elastic part is subjected to deformation, the elastic part is configured to apply a force, on the first and/or the second body parts, in a direction of increasing a separation between the first contact part and the second contact part.

A system and method of increasing efficiency and power output of a gas turbine system using a compressed air storage system including delivering a compressed air charge from the compressed air storage system, the compressed air charge having a pressure greater than ambient pressure and a temperature less than ambient temperature, the compressed air charge being delivered to the gas turbine and the compressed air charge operable to cool at least a portion of the gas turbine.

A gas turbine engine having an improved air delivery system that includes features for pressurizing and/or cooling various components of the engine while minimizing the impact to the cycle efficiency of the engine, reducing the weight of the engine, and reducing the specific fuel consumption of the engine is provided.

In one embodiment, an airfoil includes an airfoil body portion, an airfoil tip portion disposed radially outward of the airfoil body portion, an airfoil root portion, and a plurality of radial cooling passages extending through the airfoil body portion from the root portion to the tip airfoil portion. The airfoil body portion and the airfoil tip portion are joined at a braze interface or a weld interface. The airfoil tip portion includes at least one manifold fluidly connecting at least one radial cooling passage to at least one other radial cooling passage.

An engine assembly includes a combustor, a fuel cell stack integrated with the combustor, the fuel cell stack configured (i) to direct fuel and air exhaust from the fuel cell stack into the combustor and (ii) to generate electrical energy, a catalytic partial oxidation convertor that is fluidly connected to the fuel cell stack, the catalytic partial oxidation convertor being configured to optimize a hydrogen content of a fuel stream to be directed into the fuel cell stack, and one or more subsystems electrically connected with the fuel cell stack, the one or more subsystems being configured to receive the electrical energy generated by the fuel cell stack. The combustor is configured to combust the fuel and air exhaust from the fuel cell stack into one or more gaseous combustion products that drive a downstream turbine.

An engine assembly includes a combustor, a fuel cell stack integrated with the combustor, and a pre-burner system fluidly connected to the fuel cell stack. The fuel cell stack is configured to direct fuel and air exhaust from the fuel cell stack into the combustor. The pre-burner system is configured to control a temperature of an air flow directed into the fuel cell stack. The combustor is configured to combust the fuel and air exhaust from the fuel cell stack into one or more gaseous combustion products that drive a downstream turbine. The engine assembly can further include a catalytic partial oxidation convertor that is fluidly connected to the fuel cell stack. The catalytic partial oxidation convertor is configured to develop a hydrogen rich fuel stream to be directed into the fuel cell stack.

A radio frequency waveguide communication system includes a guided electromagnetic transmission network, and a cooling air source. The guided electromagnetic transmission network includes one or more remote node in fluid communication with one or more waveguides. The cooling air source is in fluid communication with the guided electromagnetic transmission network and is configured to provide pressurized cooling air to the waveguide. The waveguides direct the pressurized cooling air to the remote node.