United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Robert Newman

Jeffrey Jay Lienau

Anthony P Cherolis

Paul K Sanchez

Cheng-Zhang Wang

Rajendra Prasad Uppara Allabanda

Conway Chuong

Jorn Axel Glahn

Joshua Daniel Winn

Peter M Munsell

John S Tu

John T Ols

Clifton J Crawley, Jr

John H Mosley

Kristin Kopp-Vaughan

David F Cloud

Michelle Diana Stearns

Krishna Nelanti

Venu Sambarapu

Prabaharan Manoharan

Senthil Prasad Mathiyalagan

Flow diverters for installation in mid-turbine frame systems at a conduit outlet of gas turbine engines are described. The flow diverters include a diverter body having a connector portion defining a diverter inlet, a diverter extension at least partially defining a diverter outlet, and a curved portion arranged between the connector portion and the diverter extension, the curved portion configured to change a direction of flow from a first direction to a second direction that is about 90&#xb0; from the first direction as the flow passes from the diverter inlet to the diverter outlet.

Flow diverter for mid-turbine frame cooling air delivery

An air seal assembly for a gas turbine includes a flow path platform. The air seal assembly further includes a casing disposed radially outside the flow path platform. The air seal assembly further includes an annular finger seal mounted to the casing and disposed between the flow path platform and the casing. The annular finger seal includes a first circumferential portion mounted to the casing, a second circumferential portion extending from the first circumferential portion, and a third circumferential portion extending from the second circumferential portion and contacting an outer surface of the flow path platform. The third circumferential portion includes a plurality of air cooling holes configured to direct a cooling air stream onto the flow path platform.

Air seal assembly

A gas turbine engine includes a mid-turbine frame that includes an inner frame case. At least one spoke is connected to the inner frame case. At least one spoke includes a fluid passage that is in fluid communication with a channel on a radially inner end of the fluid passage. The channel is directed in a radially inward and circumferential direction. A cavity is located radially inward from the mid-turbine frame and is in fluid communication with the channel.

Cooling passages for a mid-turbine frame

A turbine engine includes a turbine section with a low pressure turbine and a turbine case disposed about an axis. A frame assembly defines an outer cavity and an inner cavity with the outer cavity including at least one opening configured and adapted to communicate cooling air to the turbine case. A transfer tube is disposed within the outer cavity and is configured and adapted to receive cooling air. The transfer tube includes a bend configured to impart circumferential velocity to the cooling air within the outer cavity.

Engine mid-turbine frame transfer tube for low pressure turbine case cooling

A mid-turbine frame assembly includes an inner frame case which includes a first plurality of holes and a second plurality of holes. A plurality of tie rods is circumferentially spaced around the inner frame case and includes an inlet passage that is aligned with the first plurality of holes. A plurality of hollow airfoils is aligned with the second plurality of holes.

Growing community of inventors

Harwinto, CT, United States of America

Robert Newman