General Electric Company

Elias Harry Lampes

Robert Francis Manning

Craig Robert Jacobson

Jason David Shapiro

Stephen John Howell

Gary Charles Liotta

Aaron Michael Dziech

Victor H Correia

Roger Lee Doughty

Brian Kenneth Corsetti

Clifford Edward Allen, Jr

John W Vinson

Robert Carella

Jason David Shaprio

Victor Correia

A turbine shroud apparatus is provided for a gas turbine engine having a central axis. The apparatus includes: (a) an annular support member; (b) a turbine shroud disposed in the support member, the shroud being a continuous ring comprising a low-ductility material and having opposed flowpath and back surfaces, and opposed forward and aft ends; and (c) a spring mounted between the support member and the shroud and arranged to resiliently urge the shroud to a concentric position within the structural member.

Mounting apparatus for low-ductility turbine shroud

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.

Brush seal

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.

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.

Nested bridge seal

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.

High excursion ring seal

A turbine blade includes an airfoil having opposing first and second sides and an internal passage extending longitudinally therebetween. A plurality of first turbulator ribs extend from the first side into the passage, and a plurality of second turbulator ribs extend from the second side into the passage. The first and second ribs are different in configuration from each other for obtaining different heat transfer enhancements on the first and second sides for reducing pressure losses and cooling air flow requirements.

Turbine blade having opposing wall turbulators

A turbine blade includes an airfoil having first and second opposite sides and an internal passage extending longitudinally therebetween for channeling air to cool the airfoil. A single restart turbulator rib is disposed in the passage adjacent to the inlet and has a first height e.sub.1 for obtaining a first convective heat transfer enhancement. A plurality of primary turbulator ribs are disposed downstream from the restart rib in the passage. The primary ribs include an initial primary rib having a second height e.sub.2 for obtaining a second convective heat transfer enhancement, with the initial primary rib being spaced longitudinally from the restart rib at a first spacing S.sub.1, and spaced longitudinally from a second primary rib at a second spacing S.sub.2. The first enhancement is less than the second enhancement to reduce overcooling of the airfoil between the restart and primary ribs.

Turbine blade having restart turbulators

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.

Multi-hole film cooled combuster linear with differential cooling

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.

Combustor dome plate support having uniform thickness arcuate apex with

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.

Growing community of inventors

Lynn, MA, United States of America

Elias Harry Lampes