General Electric Company

Matthew Brian Surprenant

John Alan Manteiga

David Vickery Parker

Christopher David King

Megan Lynn Williams

Awot Michael Berhe

Jesse Jacob Ollove

Paul Hadley Vitt

Brian Keith

Thomas William Vandeputte

Prem Venugopal

A turbine engine stage includes a plurality of airfoils extending between an inner band and an outer band. Each airfoil in the plurality of airfoils can have an outer wall defining a pressure side and a suction side, with the outer wall extending between a leading edge and a trailing edge. An intervening flow passage is defined between two adjacent airfoils in the plurality of airfoils.

Airfoil assembly with flow surface

A diffuser-deswirler for a gas turbine engine is provided. The diffuser-deswirler includes an inner shell and an outer shell spaced apart and configured for receiving a flow of compressed air from a compressor of a gas turbine engine. A plurality of vanes extend between the inner shell and the outer shell to define a plurality of fluid passageways and a splitter extends along the circumferential direction between adjacent vanes to split the flow of compressed air passing through the each fluid passageway. All of these components are manufactured as a single monolithic piece and are configured for diffusing and deswirling compressor air before passing it to a combustor for an improved combustion process.

Diffuser-deswirler for a gas turbine engine

Growing community of inventors

Stoneham, MA, United States of America

Matthew Brian Surprenant