General Electric Company

Anquan Wang

Craig Alan Gonyou

Ryan Christopher Jones

Guanghua Wang

Paul Christopher Schilling

Michael Anthony Benjamin

Shai Birmaher

Nirm Velumylum Nirmalan

Hejie Li

Hiranya Kumar Nath

Kwanwoo Kim

Samhita Dasgupta

Nayan Vinodbhai Patel

Duane Douglas Thomsen

Daniel J Kirtley

Eric John Ruggiero

Wilbur Douglas Scheidt

Edward Randall Furlong

Nicholas John Bloom

Gerardo Antonio Salazar Lois

James DeLancey

Hojjat Nasr

Jordi Estevadeordal

Chad Holden Sutton

Harris Daniel Abramson

Robert Andrew Stowers

Trevor James Hahm

James A Russo

Shanwu Wang

Sean Patrick Harper

Habeeb Kunnummal Manat

Jeffrey Lehmkuhl

Bradford Allen Lewandowski

Rodrick Gordon Brown

Stephen Thomas Walls

An apparatus relating to a component for a turbine engine which generates a hot gas fluid flow, and provides a cooling fluid flow. The component having a wall separating the hot gas fluid flow from the cooling fluid flow and having a heated surface along which the hot gas fluid flow flows and a cooled surface facing the cooling fluid flow. At least one cooling hole including a connecting passage extending from a first inlet located at the cooled surface, to a first outlet located at the heated surface, the connecting passage defining a downstream flow direction from the first inlet to the first outlet, the connecting passage comprising a metering section fluidly coupled to the first inlet and defining a metered centerline and a diffusing section, downstream of the metering section, defining a diffused centerline, and fluidly coupling the metering section to the first outlet.

Component for a turbine engine with a cooling hole

A combustor of a turbine engine has a combustion chamber for combusting fuel and air, generating heat. A fuel nozzle-mixer assembly mixes and injects fuel and air into the combustion chamber for combustion. The assembly has a heat shield at an aft end for shielding the assembly from the heat. A centerbody outer shell defines a cooling air flow cavity. A cooling air flow gap is defined between the centerbody outer shell and the heat shield. The centerbody outer shell has cooling air exit holes between the cooling air flow cavity and the cooling air flow gap, the air passing through the cooling air exit holes and into the cooling air flow gap. The cooling air exits the cooling air flow gap at a cooling air exit angle, the cooling air exit angle having a non-zero axially aft component, displacing the combustion downstream, to protect the assembly.

Turbine engine combustor including a heat shield

An apparatus, system, and method of reducing film cooling scrubbing in a combustor are provided. The apparatus includes a combustor liner that includes a field of a plurality of sparsely-spaced film holes that extend through the combustor liner wherein the field includes a boundary. The combustor liner also includes a patch of relatively more densely-spaced shield holes that extend through the combustor liner at specific predetermined locations within the boundary of the field.

Combustor liner with shield holes

An apparatus and method relating to a cooling hole of a component of a turbine engine. The component can include a wall separating the hot gas fluid flow from the cooling fluid flow and having a heated surface along which the hot gas fluid flow flows and a cooled surface facing the cooling fluid flow and at least one cooling hole comprising at least one inlet at the cooled surface, at least one outlet at the heated surface, with the outlet having a modified outlet shape.

A combustor for a turbomachine engine includes a dome made of a ceramic matrix composite (CMC) material, the dome being secured within a support structure. The combustor includes an outer liner made of the CMC material, the outer liner being secured to the dome within the support structure. The combustor also includes an inner liner made of the CMC material, the inner liner being secured to the dome within the support structure.

Ceramic composite combustor dome and liners

A combustor assembly for a turbine engine and method for cooling a portion of the combustor assembly, the combustor assembly comprising a combustor liner defining a combustion chamber with an inlet and an outlet, a fuel dome located in the inlet and having a wall adjacent at least a portion of the combustor liner, and a deflector overlying and spaced from at least a portion of the wall.

Turbine engine with combustor

An engine component is generally provided for a gas turbine engine generating hot combustion gas flow. In one embodiment, the engine the engine component includes a substrate having a hot surface facing the hot combustion gas flow and a cooling surface facing a cooling fluid flow. The substrate defines a film hole extending through the substrate and having an inlet provided on the cooling surface, an outlet provided on the hot surface, and a passage connecting the inlet and the outlet. The passage defines a diffusion section having a pair of side passage walls extending to the outlet on the hot surface, with each of the side passage walls within the diffusion section having a surface roughness (Ra) of about 4 mils to about 7 mils. Methods are also provided for forming a film hole in a CMC substrate.

CMC articles having small complex features for advanced film cooling

A system for use in inspecting a component having flow openings defined therein. The system includes a fluid injector in flow communication with the component, wherein the fluid injector provides fluid to the component such that the fluid is discharged from the flow openings. A sensing sheet is coupled to or positioned proximate to the component such that the fluid discharged from the flow openings is received at the sensing sheet, wherein the sensing sheet is formed from pressure-sensitive material. A light source emits light towards the sensing sheet such that the pressure-sensitive material is excited to an energy level. The system further includes an imaging device that captures images of a change in color of the pressure-sensitive material as a function of a pressure of the fluid received at the sensing sheet, wherein the change in color represents a pressure distribution across the sensing sheet based on a flow profile of the fluid discharged from the flow openings.

System and methods of inspecting a component

A combustor assembly for a gas turbine engine defining an axial direction is provided. The combustor assembly generally includes a liner, an annular dome, and a deflector plate. The liner at least partially defines a combustion chamber. The annular dome defines a first cavity and has a plurality of impingement holes, and the deflector plate defines a conical surface and a flat surface, wherein a plurality of cooling holes are defined through the deflector plate. The annular dome and the deflector plate are positioned together to define a second cavity that is in fluid communication with the first cavity through the plurality of impingement holes. In addition, the second cavity is in fluid communication with the combustion chamber through the plurality of cooling holes.

Sealed conical-flat dome for flight engine combustors

An optical sensor system includes a multi-color pyrometer in optical communication with a component. The pyrometer generates signals at least partially representative of radiation received from the component and from soot particles. The system includes at least one processing unit coupled to the pyrometer. The processing unit is programmed to receive the signals and distinguish portions of radiation received between at least two wavelength bands. The processing unit is also programmed to determine that a first portion of radiation within a first of the wavelength bands is representative of a temperature of soot particles and that a second portion of radiation within a second of the wavelength bands is representative of a temperature of the component. The processing unit is further programmed to filter out signals representative of the first portion of the radiation.

Optical sensor system for a gas turbine engine and method of operating the same

A thermal measurement system that includes a light collection device and a detection system in communication with the device. The detection system includes two detection subsystems, wherein one subsystem is configured to detect light from a surface of an object, while the other subsystem is configured to detect light from the surface and a gas. The present invention has been described in terms of specific embodiment(s), and it is recognized that equivalents, alternatives, and modifications, aside from those expressly stated, are possible and within the scope of the appending claims.

Multiwavelength thermometer

Growing community of inventors

Mason, OH, United States of America

Anquan Wang