Siemens Energy, Inc.

Siemens Aktiengesellschaft

University of Central Florida Research Foundation Inc

Arindam Dasgupta

Anand A Kulkarni

Ahmed Kamel

Amit Chakraborty

Nina Orlovskaya

Anthony C Terracciano

Biswadip Dey

A small-scale thermoelectric power generator and combustion apparatus, components thereof, methods for making the same, and applications thereof. The thermoelectric power generator can include a burner including a matrix stabilized combustion chamber comprising a catalytically enhanced, porous flame containment portion. The combustion apparatus can include components connected in a loop configuration including a vaporization chamber; a mixing chamber connected to the vaporization chamber; a combustion chamber connected to the vaporization chamber; and a heat exchanger connected to the combustion chamber. The combustion chamber can include a porous combustion material which can include a unique catalytic material.

Thermoelectric power generator and combustion apparatus

A computer-implemented method for assessing material microstructure of a machine component involves obtaining a raw image of a section of the component captured via a microscope. The method further includes pre-processing the raw image to generate a ternary image defined by pixel data including three levels of intensities. The method further includes identifying, from the ternary image, phase boundaries delineating at a phase in a primary constituent material of the component. The method further includes determining a volume associated with the phase based on the identified phase boundaries. The proposed method may be utilized, for example, as an automated tool for assessing material degradation and for quality control of gas turbine engine components.

System and method for automated microstructure analysis

A turbine blade includes a platform with an internal cavity formed therein and an airfoil extending radially from the platform. The turbine blade includes a first portion made from ceramic matrix composite materials and a second portion made from superalloy materials. The first and second portions are selectively connected to each other via a spur and include an internal cooling circuit extending across both the first and second portions for circulating coolant therethrough. At least one supply passage extends between the internal cooling circuit and the internal platform cavity and includes an array of pin fins and turbulators for diverting coolant to the internal platform cavity.

Metal trailing edge for laminated CMC turbine vanes and blades

A turbine blade having an airfoil portion includes a first ceramic matrix composite (CMC) component having a first outer surface and a second ceramic matrix composite (CMC) component having a second outer surface. The second CMC component is positioned adjacent the first CMC component such that the first outer surface and the second outer surface align with one another and at least partially define the airfoil portion. A ceramic bead is at least partially formed at an interface between the first CMC component and the second CMC component. The formation of the bead melts a portion of the first CMC component and the second CMC component, such that the ceramic bead, the first CMC component, and the second CMC component become a single contiguous component and the bead fixedly attaches the first CMC component and the second CMC component. The bead includes a bead outer surface that extends outward beyond the first outer surface and the second outer surface and an overlayer is deposited onto the airfoil portion, the overlayer bonded to the first outer surface, the second outer surface, and the bead outer surface.

Growing community of inventors

Avon, CT, United States of America

Arindam Dasgupta