General Electric Company

Anne M Isburgh

Ching-Pang Lee

Paul Stuart Wilson

Vinay Bhaskar Jammu

Mohamed Ahmed Ali

Gulcharan Singh Brainch

Ajay Kumar Behera

John Joseph Madelone, Jr

Nicholas Damlis

Edward H Goldman

James A Martus

Alan L Webb

Theodore T Thomas, Jr

Khan Mohamed Khirullah Genghis Khan

Omprakash Velagandula

Ali Osman Ayhan

Donald George La Chapelle

An embodiment of a method for lifespan modeling for a turbine engine component includes determining a design-phase model of the lifespan of an turbine engine component; fusing the design-phase model with sensor data collected during operation of the turbine engine component to produce an updated model of the lifespan of the turbine engine component; and fusing the updated model with data collected during an inspection of the turbine engine component to produce an overall model of the lifespan of the turbine engine component. Systems for lifespan modeling for a turbine engine component are also provided.

Physics-based lifespan modeling

The flow of cooling fluid through a core tie hole formed between a pair of internal cooling passageways of an airfoil component is reduced by providing a restriction that meters coolant flow through the inlet passage of one of the passageways so that the pressures in the two passageways are equalized, thereby minimizing the flow of cooling fluid through the hole. The restriction can be a metering plate disposed at the entrance of the inlet passage or a restriction integrally formed in the inlet passage.

Airfoil component having internal cooling and method of cooling

A turbine blade includes an airfoil having an internal cooling circuit therein. The airfoil extends from a root to a tip cap, and includes laterally opposite pressure and suction sides extending between a leading edge and an opposite trailing edge over which is flowable a combustion gas. A pair of squealer tips extend radially upwardly from the tip cap along the pressure and suction sides, and are spaced apart between the leading and trailing edges to define an upwardly open tip cavity. At least one of the squealer tips includes a slot extending radially inwardly to the tip cap, with the slot also extending along the squealer tip between the leading and trailing edges. A plurality of spaced apart supply holes extend radially through the tip cap in the slot in flow communication with the cooling circuit for channeling the coolant into the slot for cooling the squealer tip. A thermal barrier coating may then be disposed on an outboard side of the squealer tip for providing insulation against the combustion gas flowable therealong.

Slot cooled blade tip

An airfoil blade, such as a jet engine turbine rotor blade. An internal serpentine coolant circuit has a last downstream passageway bounded by four monolithic inner walls which are monolithic with at least a portion of the outer walls. Two of the inner walls are spaced from the outer walls and contain air impingement orifices creating two impingement chambers. Some coolant in the serpentine circuit exits the airfoil blade through a coolant exit in the blade tip. The remaining coolant in the circuit passes through the impingement orifices and exits the blade through film cooling holes in the outer walls.

Airfoil blade having a serpentine cooling circuit and impingement cooling

A coolable airfoil for use in gas turbine engine component such as a turbine blade or vane is provided with a radially extending airfoil having an outer wall surrounding at least one radially extending cavity and extending chordwise through at least a portion of the airfoil. The outer wall has ribs disposed on an inner surface of the outer wall and cooling passages formed between the outer wall and an insert disposed in the cavity against and in abutting sealing relationship with the ribs, wherein the outer wall is formed from two radially and chordwise extending sections, preferably suction and pressure side sections, bonded together while the insert was disposed inside the cavity. The insert provides an inner wall surrounding a hollow chamber generally conforming to the cavity the insert is disposed in and the insert includes a spring to force the inner wall out against the ribs during the bonding process.

Bonded turbine airfuel with floating wall cooling insert

A coolable airfoil for use in gas turbine engine component such as a turbine blade or vane is provided with a one-piece integrally formed double shell outer wall surrounding at least one radially extending cavity. The inner and the outer shells are integrally formed of the same material together with tying elements in the form of continuous ribs which space apart the shells, mechanically and thermally tie the shells together, and form convective cooling passages therebetween.

Turbine airfoil with convectively cooled double shell outer wall

An airfoil for a gas turbine engine is constructed from a core body formed of a conventional nickel-based superalloy and leading and trailing edge components and squealer tip formed of a nickel aluminide alloy. The nickel aluminide components exhibit a high degree of thermal conductivity and efficiently transfer heat into the core body by direct conduction.

Bimetallic turbine airfoil

A jet engine component includes a body having a wall portion with an external surface exposed to hot gas flow and an internal surface exposed to a cooling air flow. The engine component incorporates an arrangement of cooling holes defined through the wall portion between the external and internal surfaces thereof to permit flow of cooling air from the hollow interior through the wall portion to the exterior of the component. Each cooling hole includes at least one flow inlet at the internal surface of the wall for receiving the cooling air flow, at least a pair of flow outlets at the external surface of the wall for discharging the cooling air flow, and at least a pair of flow branches extending through the wall portion and between the flow inlet and the flow outlets for permitting passage of the cooling air flow from the flow inlet to the flow outlets. In one V-shaped configuration, the flow branches merge and intersect with one another at the flow inlet. In another X-shaped configuration, there are a pair of flow inlets and the flow branches merge and intersect with one another at a location intermediate between and spaced from the flow inlets and outlets. The flow outlets are displaced preferably downstream of the flow inlet relative to the direction of gas flow past the external surface of the wall of the engine component.

Growing community of inventors

Loveland, OH, United States of America

Anne M Isburgh