United Technologies Corporation

John A Matthews

Francis C Pane, Jr

Robert E Coburn

Edmund E Striebel

Richard R Wright

Domingo Sepulveda

Melvin H Zeisser

Thomas Frasca

John M Sarnik

Vito J Sarli

David A Washburn

A seal assembly secured to the downstream end of a gas turbine engine combustor liner forms a gas path seal at the upstream facing platforms of turbine inlet guide vanes and also cools the vane platforms. The seal assembly includes an annular coolant compartment which feeds cooling air to a plurality of circumferentially spaced apart, axially extending open-ended channels formed between a conical portion of the downstream-most combustor liner and an annular baffle member disposed on the non-gas path side of the conical liner. The seal assembly is supported and axially located on a cylindrical surface which permits locating the seal assembly such that the downstream end of the conical liner is closely spaced from the turbine inlet guide vane platforms to reduce leakage from the gas path. The open-ended channels are also closely spaced from the vane platforms and located to direct high velocity coolant fluid against the upstream facing surfaces of the platforms at circumferential locations where the pressure in the gas path is highest, thereby further reducing leakage from the gas path.

Sealing and cooling arrangement for combustor vane interface

A fuel injector assembly for a gas turbine combustor projects a hollow conical spray of fuel. A plurality of discrete surrounding air nozzles 42 project air directly toward the axis 46 of the injector at an angle of 15 degrees, establishing a fuel rich external recirculation zone 52.

Airblast fuel injector

A sliding expansion joint (68) for the interface between an annular combustor head (24) and a downstream-extending liner (47) of a combustion chamber (18) includes an inward facing cylindrical surface (78) on the head (24) and a thickened upstream ring (74) in the liner (47). A cooled, radially extending bulkhead (36) isolates the joint (68) thermally from the high temperature combustion reaction (50). A region of reduced static air pressure is induced adjacent the joint (68) by the flow of air (86) over the convex combustor dome (30). Any air leakage through joint (68) adds to the existing flow of cooling air (106) adjacent the liner (47).

Sliding joint for an annular combustor

A sealing device which is adapted to cooperate with and be secured to the outwardly extending tabs on the inlet vanes for the turbine in which the tabs provide a forwardly facing surface and the sealing device has a rearwardly facing surface in contact with one another and with the parts secured together by a row of bolts in which the sealing element has a flange along the outer edge of the element between certain bolts to reinforce the plate and between other bolts the sealing element is reinforced by plates extending between adjacent bolts and secured to the forward side of the sealing element by said bolts.

Combustion chamber rear outer seal

A fuel nozzle for a gas turbine engine is constructed with two major castings where one is the support and the other is the head, both welded together adjacent the fuel orifice plate. The fuel passage is cast into the support providing a smooth radius from the radial to axial flow path and a smooth transition from the circular to the annular cross section. This configuration allows dimension control over the filming lip and other critical dimensions of the nozzle.

Fuel nozzle for gas turbine engine

This invention minimizes wakes manifested by a fuel nozzle support structure extending through an annular diffuser engine to the burner in a gas turbine engine, spaced walls extending from the inner and outer wall of the diffuser project toward the nozzle support downstream of the support that passes transverse to the flow, one wall being shaped conically and the other being shaped bell-mouthed and convergent.

High blockage diffuser with means for minimizing wakes

This invention relates to the construction of the fuel nozzle guide of a turbine power plant and provides sealing while allowing relative movement between the fuel nozzle and combustion liner, and includes the judicious location of cooling passages that permit constant cooling and purging for preventing local hot spots resulting from unwanted flame holding.

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Melrose, CT, United States of America

John A Matthews