Abstract: A double brush seal for sealing the combustor-turbine nozzle interface of a gas turbine engine includes a stationary support member and an intermediate plate attached to the stationary support member. The brush seal also includes a first end plate located upstream of the intermediate plate and attached to the stationary support member, and a second end plate located downstream of the intermediate plate and attached to the stationary support member. A first bristle pack is disposed between the first end plate and the intermediate plate, and a second bristle pack is disposed between the second end plate and the intermediate plate such that the intermediate plate functions as a common back plate for the two stages of the seal.

Abstract: A brush seal for sealing a leakage path located between a rotating member and a stationary member includes an intermediate plate attached to the stationary member and having at least one purge hole formed therein. The brush seal also includes a first end plate attached to the stationary member on one side of the intermediate plate and a second end plate attached to the stationary member on the other side of the intermediate plate. A first bristle pack is disposed between the first end plate and the intermediate plate, and a second bristle pack is disposed between the second end plate and the intermediate plate.

Abstract: A seal includes a seal ring with a circumferential split defining a gap. An arcuate bridge extends across the gap and nests in the seal ring. The bridge includes an anchor end which engages the seal ring solely in friction to restrain differential circumferential movement therebetween. The bridge also includes a slip end engaging the seal ring on an opposite side of the gap with less friction than the anchor end to permit differential circumferential movement therebetween.

Abstract: A seal includes first and second axially opposite loops integrally joined together by a coextensive web in a collective ring having a circumferential split. The two loops are arcuate in section, with radially outer and inner sealing lands. And, the web is disposed radially between the outer and inner lands. The loops are disposed in corresponding grooves of adjoining members for effecting a seal therebetween and accommodating differential radial and axial thermal movement.

Abstract: A gas turbine engine combustor is provided with a single wall sheet metal liner having a generally annular shape, which may be corrugated, and contains at least one differential pattern of multi-hole film cooling holes. The differential pattern of cooling holes comprises patterns of small closely spaced sharply downstream angled film cooling holes disposed along portions of the liner so as to direct different amounts of film cooling air to different areas of the liner to accommodate differential heating along the liner. One embodiment of the invention includes a plurality of superimposed differential cooling hole patterns derived from a base pattern wherein each preferential pattern is formed by skipping patterns of cooling holes in the base pattern.

Abstract: A combustor dome includes an annular dome plate having a plurality of circumferentially spaced apertures in a central portion thereof for receiving a plurality of carburetors. The dome plate also includes outer and inner support portions for joining the dome plate to combustion liners. Each of the support portions include a first leg extending from the central portion, a second leg, and an arcuate apex joining the first and second legs. The apex has a uniform thickness and includes a plurality of circumferentially spaced coolant apertures for channeling cooling air therethrough.

Abstract: An improved air swirler and fuel injector for a gas turbine combustor system employs primary fuel injection into a primary recirculation combustion zone supplied by an inner annulus of swirling air at high fuel-air ratio under low power conditions. A selectively staged secondary fuel flow is supplied into an outer annulus downstream of secondary air swirlers supplying a secondary recirculation zone for combustion at higher fuel flows but lower fuel-air ratios under high power conditions. The secondary fuel flow may be separately injected into the outer annulus through conduit means extending through the primary air swirler vanes. Alternatively, the secondary fuel flow may be combined with the primary fuel in the fuel injector body and the momentum due to mass flow used to inject the fuel into the outer annulus.