Rolls-royce North American Technologies Inc.

Rolls-royce Corporation

Gm Global Technolgoy Operations, Inc.

Emil R Dejulio

James Carl Loebig

Aaron D Sippel

Jun Shi

Bryan H Lerg

Eric Sean Donovan

James E McDonald

Chandran Bhala Santanam

Stephen A Bergeron

Christopher J Bies

William H Thomas

Jefre H Cockerham

A microchannel heat exchanger (MCHX) includes an air-passage layer including a plurality of air-passage microchannels, a working fluid layer including a plurality of working fluid microchannels, and a sealing layer coupled to the working fluid layer to provide a working/sealing layer set. The working/sealing layer set includes an arrangement of raised pedestals. The raised pedestals may extend from the working fluid layer to the sealing layer and contact the sealing layer.

Microchannel heat exchangers for gas turbine intercooling and condensing

A gas turbine engine heat exchange system includes a first microchannel heat exchanger (MCHX) configured to transfer heat between a first air stream and a working fluid. The first MCHX includes a plurality of air-passage layers. Each of the air-passage layers includes a plurality of etched air-passage microchannels that are configured to allow passage of the first air stream therethrough. The first MCHX also includes a plurality of working fluid layers. Each working fluid layer includes a plurality of etched working fluid microchannels that are configured to allow passage of the working fluid therethrough.

A gas turbine engine heat exchange system including a first multi-width channel heat exchanger (MWCHX) configured to transfer heat between a first air stream and a heat transfer fluid. The first MWCHX includes a first plurality of air-passage mini-channels configured to allow passage of the first air stream therethrough, where each air-passage channel has an air-channel width and an air-channel length greater than the air-channel width. The MWCHX also includes a first plurality of heat transfer fluid channels configured to allow passage of the heat transfer fluid therethrough, where each heat transfer fluid channel has a heat transfer channel width and a heat transfer channel length greater than the heat transfer channel width. The heat transfer channel width is less than the air-channel width.

Single phase micro/mini channel heat exchangers for gas turbine intercooling

A turbine shroud for use in a gas turbine engine that includes a metallic carrier, a blade track, and a seal is disclosed. The seal is engaged with surfaces of the metallic carrier and the blade track to block ingress of hot gasses at the interface of the blade track and the metallic carrier.

Seals for gas turbine engines

One embodiment of the present invention is a unique system for measuring radiant energy in gas turbine engines, gas turbine engine components and gas turbine engine/component rigs. Another embodiment is a unique method for measuring radiant energy in gas turbine engines, gas turbine engine components and gas turbine engine/component rigs. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for measuring radiant energy. Further embodiments, forms, features, aspects, benefits, and advantages of the present application shall become apparent from the description and figures provided herewith.

System and method for measuring radiant energy in gas turbine engines, components and rigs

An exhaust device is disclosed that includes a duct that turns an exhaust flow from a gas turbine engine from a first direction to a second direction. A diverter cup is disposed within the duct and serves to split the exhaust flow into two streams as well as introduce cooling air through an ejector pump at the downstream end of the diverter cup. A splitter is disposed downstream of the diverter cup and serves to split the cooling air into two streams which are thereafter mixed with the split exhaust flow. A diffuser is created in the exhaust device between the duct and the splitter. Various cooling slots are also provided in the duct.

Gas turbine exhaust assembly

An external combustor for a gas turbine engine has a cyclonic combustion chamber into which combustible gas with entrained solids is introduced through an inlet port in a primary spiral swirl. A metal draft sleeve for conducting a hot gas discharge stream from the cyclonic combustion chamber is mounted on a circular end wall of the latter adjacent the combustible gas inlet. The draft sleeve is mounted concentrically in a cylindrical passage and cooperates with the passage in defining an annulus around the draft sleeve which is open to the cyclonic combustion chamber and which is connected to a source of secondary air. Secondary air issues from the annulus into the cyclonic combustion chamber at a velocity of three to five times the velocity of the combustible gas at the inlet port. The secondary air defines a hollow cylindrical extension of the draft sleeve and persists in the cyclonic combustion chamber a distance of about three to five times the diameter of the draft sleeve. The hollow cylindrical extension shields the drive sleeve from the inlet port to prevent discharge of combustible gas through the draft sleeve.

Growing community of inventors

Columbus, IN, United States of America

Emil R Dejulio