A method for operating a gas turbine engine includes channeling compressed air from the gas turbine engine to a noise suppression system, and selectively operating the noise suppression system such that air discharged from the noise suppression system generates a plurality of flow control mechanisms in the gas turbine exhaust flowpath

Methods and apparatus for operating gas turbine engines

A method of operating a gas turbine engine is provided. The gas turbine engine includes at least one engine casing and at least one rotor assembly. The method includes directing airflow through a supply pipe and into a heat exchanger, lowering the temperature of the airflow in the heat exchanger, and directing the cooled airflow into the engine casing to cool the casing.

Methods and apparatus for maintaining rotor assembly tip clearances

Aspects of the invention relate to a system and method for actively controlling compressor clearances in a turbine engine by passing a thermal fluid in heat exchanging relation through a compressor vane carrier. During some operational conditions, such as hot restart or spin cool, it may be desirable to heat the vane carrier to enlarge or at least prevent a decrease in compressor clearances. In such cases, a heated thermal fluid can be provided by reclaiming residual exhaust energy from a heat recovery steam generator. At any condition where improved performance is desired, such as at base load operation, the vane carrier can be cooled to minimize compressor clearances. A cooled thermal fluid can be bleed air from an upstream portion of the compressor, water-cooled high pressure bleed air from a downstream portion of the compressor, or feed water from the bottoming cycle in a combined cycle engine.

System for actively controlling compressor clearances

A composite annular shroud (42) supported by a support assembly (46) including at least two single piece full 360 degree rings (50, 52, 54 or 130) and at least partially disposed within an innermost one of the rings. The shroud (42) is biased against and in sealing engagement with an inner flange (84) of the innermost ring. A three ring assembly includes the inner ring (50) disposed radially inwardly of a middle ring (52) disposed radially inwardly of an outer ring (54) and the shroud (42) at least partially disposed within the inner ring (50). At least three clocking pins (74) extend radially inwardly from the middle ring (52) through slots (76) in the inner ring (50) into notches (78) in the shroud (42). The middle ring (52) may be an aft end (70) of a support ring (68) fixedly connected to an engine backbone (58). Mounting pins (104) may be press fitted into pin holes (106) in the middle ring (52) and extend radially outwardly from the middle ring (52) through radial holes (107) in the outer ring (54).

Continuous ring composite turbine shroud

A gas turbine engine includes an active clearance control (ACC) system within the engine casing (52). The case (52) includes a wall structure with a cast-in cooling configuration (68) through Refractory Metal Core technology which is tailored to address traditional hot spots and improve discrete control of case growth.

Gas turbine engine case for clearance control

A gas turbine engine including an active clearance control system that facilitates extending a useful life of a rotor assembly in a cost effective and reliable manner is described. The engine includes at least one rotor assembly and an engine casing that extends circumferentially around the rotor assembly, such that a tip clearance is defined between the rotor assembly and the engine casing. The clearance control system includes a plurality of panels that couple to extend circumferentially around the engine. Each clearance control system panel includes a circumferential feed duct that is formed integrally with the panel.

A seal assembly for a fluid coupling includes: (a) a generally planar, substantially rigid seal retainer (42) with opposed first and second faces, having an annular first groove (48) formed in the first face; (b) a first resilient seal (56) disposed in the first groove (48); and (c) an annular first backup ring (58) positioned radially outboard of the first resilient seal (56) and secured to the first resilient seal (56), wherein the first backup ring (58) is substantially harder than the first resilient seal (56)

Extrusion resistant gasket face seal

A tube clamping assembly for securing tubes against movement has a bracket and a strap clamp for clamping a tube to the bracket. The strap clamp is configured to be sufficiently flexible so as to close large clamp gaps. In one embodiment, the strap clamp has a generally U-shaped portion having a pair of angled leg sections connected to a flat section. Each one of the angled leg sections forms an obtuse angle at about its midpoint so as to define an inner segment, which is connected to the flat section, and an outer segment. The inner segment of each angled leg section forms an obtuse angle with the flat section, and the outer segments are substantially perpendicular to the flat section. The U-shaped portion has a mounting flange extending from each one of the angled leg sections for bolting the strap clamp to the bracket.

Robust tube strap clamp

A heat exchanger system includes a duct having a duct wall with a duct wall outer surface and a duct wall inner surface; and a heat exchanger partial shell hermetically joined to the duct wall inner surface. The heat exchanger partial shell and a shell portion of the duct wall inner surface constitute a heat exchanger. A heat exchanger inlet manifold is defined by a nonplanar inlet sheet of material hermetically joined to the duct wall outer surface. A heat exchanger outlet manifold is defined by a nonplanar outlet sheet of material hermetically joined to the duct wall outer surface. A heat exchanger inlet opening extends through the duct wall between the inlet manifold and the heat exchanger, and a heat exchanger outlet opening extends through the duct wall between the outlet manifold and the heat exchanger.

Heat exchanger system having manifolds structurally integrated with a duct

MULTI-POINT TUBE CLAMP A clamp for mounting a tube to a support plate in a gas turbine engine includes a base plate and a capture plate for capturing the tube therebetween, with a fastener positionable through the base and capture plates for clamping them together and mounting the tube to the support plate. The base plate includes a first recess therein for receiving the tube, which recess includes three adjoining sides sized and configured for contacting the tube at two points.

Scott Richard Zearbaugh

Papers

Methods and apparatus for maintaining rotor assembly tip clearances

Extrusion resistant gasket face seal

Robust tube strap clamp

Heat exchanger system having manifolds structurally integrated with a duct

Multi-point tube clamp