Abstract: 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.

Abstract: 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.

Abstract: 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).

Abstract: The area ruling of an annular diffuser disposed between the compressor and burner of a gas turbine engine is proportioned in a circumferential direction so that the maximum area ruling is adjacent the struts supporting the diffuser walls and the minimum is mid-way between the struts so as to achieve a substantial uniform velocity profile of the exiting air in the circumferential direction.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.CROSS REFERENCEThis invention is related to the invention disclosed in copending patent application entitled FUEL NOZZLE GUIDE HEAT SHIELD FOR A GAS TURBINE ENGINE, filed by S. C. Peterson, L. W. Stevens and I. S. Tanrikut on even date and assigned to the same assignee of this application.

Abstract: Coupling means, for example for use in the furniture industry, comprises a body member having a threaded opening which communicates with an internal cavity; an elongate headed member, a shank portion of which is receivable through a slot formed in the side of the body member with its head retained within the cavity; and a threaded member receivable in the threaded opening and adapted to bear against the head of the headed member. The interior of the cavity is so shaped that tightening of the threaded member in the opening is arranged to draw the shank of the headed member further through the slot into the interior of the cavity.