Rolls-royce Corporation

Arthur B Griffin

David H Taylor

David W Tuson

Ian W Harrogate

Jeffrey D Willis

Bryan L Belcher

Bernard W Boyce

Bryan L Bechlher

A cooling and sealing arrangement in a gas turbine engine comprises a seal assembly extending between nozzle guide vanes and combustion chamber discharge nozzles. The nozzle guide vanes have platforms having extensions which in one embodiment overlap the downstream ends of the discharge nozzles. Cooling air is supplied to the upstream edge portions of the platforms through holes in flanges on the discharge nozzles. The seal assembly defines a chamber adjacent the platform extensions which is supplied with cooling air through metering holes in the seal assembly which provides part of a boundary for a cooling air chamber, the boundary of the chamber having cooling air holes for metering cooling air into the chamber to cool the upstream portion of the nozzle guide vane outer platforms. Cooling air exits the chamber through holes in the platform extensions to film cool them.

Sealing structures for gas turbine engines

A cooling and sealing arrangement in a gas turbine engine comprises a seal assembly (42,30) extending between nozzle guide vanes (20) and combustion chamber discharge nozzles (22). The nozzle guide vanes (20) have platforms (34,36) having extensions (34A,36A) which in one embodiment overlap the downstream ends of the discharge nozzles (22). Cooling air is supplied to the upstream edge portions of the platforms through holes (26,28C) in flanges (24,28) on the discharge nozzles (22). The seal assembly (42,30) defines a chamber (58,70) adjacent the platform extensions which is supplied with cooling air through metering holes (56,68) in the seal assembly. Cooling air exits the chamber (58,70) through holes (34B,36B) in the platform extensions to film cool them.

A gas turbine engine component support assembly (30) comprises a pair of ring members (64) and (74) defining a slot in which a cranked flange (28) extending from the inner surfaces of an array of combustion chamber discharge nozzles (22) is located. One part (28B) of the cranked flange has projections (28C) which engage with radial slots (76) formed in one of the ring members (74) to provide cross-key location of the discharge nozzles. The support assembly (30) is located adjacent the radially inner platform of an array of nozzle guide vanes (20), and also provides support and location for the vanes.

Gas turbine engines

Combustion chamber assembly with hollow support strut for carrying

A diffuser for use in a gas turbine engine comprises an inner and an outer annular wall which define a divergent flow passage. The divergent flow passage is divided by a splitter to form two annular flow ducts, of different flow area. Introduction of the splitter into the diffuser to form the two annular flow ducts enables the length of the outer annular wall of the diffuser to be reduced. Reducing the length of the outer annular wall of the diffuser increases the flow area between the diffuser and combustion chamber. Air downstream of the diffuser is therefore unrestricted and moves radially outward to the ports in the head of the combustion chamber with minimum pressure loss.

Air flow diffuser with path splitter to control fluid flow

An injector which is suitable for the injection of fuel and steam into the combustion apparatus of a gas turbine engine. The injector defines a substantially circular cross-section chamber having upstream and downstream ends through which steam operationally flows. Steam is supplied to the upstream end of the chamber in such a manner that it is urged into a vortex as it passes through the chamber. The downstream end of the chamber is outwardly flared so that the steam flow is exhausted from the injector in a genenrally conical configuration.

Injector

A dual fuel injector for a gas turbine engine is arranged to maintain pre-determined air fuel ratios in adjacent upstream and downstream opposite handed vortices and to reduce the deposition of carbon on the injector. The injector comprises a central duct, a deflecting member, a first radially directed outlet, and a shroud which defines an annular duct, and a second radially directed outlet. The ducts receive a supply of compressed air and the central duct receives gaseous fuel from an annular nozzle and the annular duct receives liquid fuel from a set of nozzles. When the injector is operating on liquid fuel, the fuel and air mixture issues from the second outlet and compressed air flows from the first outlet and prevents migration of fuel between the two vortices, thereby maintaining a rich air fuel ratio in the upstream vortex which reduces the emissions of NOx. Also, the flow of air from the first outlet reduces the deposition of carbon from the liquid fuels on the deflecting member.

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Leicestershire, United Kingdom

Arthur B Griffin