203 results about "Thermal growth" patented technology

A mounting assembly for an aft end of a liner of a gas turbine engine combustor including a support member, wherein a longitudinal centerline axis extends through the gas turbine engine. The mounting assembly includes a pin member extending through each one of a plurality of circumferentially spaced openings in a portion of the support member for the combustor and into a plurality of partial openings formed in the aft end of the liner, with each pin member including a head portion at one end thereof, and a device positioned within each opening in the support member so as to retain the pin members therein. The pin members and the support member are able to slide radially and/or axially with respect to the liner aft end as the support member experiences thermal growth greater than the liner.

A mounting arrangement (10) for a multivane segment (12) of ceramic matrix composite (CMC) composition positioned between outer and inner metallic rings (14, 16). Selected ones of the vanes (18a) of the multivane segment surround internal struts (24) joining the outer and inner rings. Spring members (26, 28) accommodate differential thermal growth between the multivane segment and the outer and inner rings, and a compliant material (30) seals against gas leakage around the segments.

A mounting assembly for a forward end of a liner in a combustor of a gas turbine engine including a dome and a cowl, wherein a longitudinal centerline axis extends through the gas turbine engine. The mounting assembly includes a pin member extending through each one of a plurality of circumferentially spaced openings formed in the forward end of the liner, an aft portion of the cowl, and a portion of the dome, with each pin member including a head portion at one end thereof. A nut is adjustably connected to an end of each pin member opposite the head portion. A bushing is located on each pin member at a position intermediate the head portion and the nut, wherein the openings in the liner forward end are sized to fit around the bushings. In this way, the cowl aft portion and the dome portion are fixedly connected together between the bushing and the nut so that the bushings are able to slide radially through the openings in the liner forward end as the cowl and the dome experience thermal growth greater than the liner.

A system and method for determining thermal growth of motor or engine parts to thereupon control the clearance of motor or engine fan blades is disclosed herein. In addition, a system and method for monitoring the health of a turbine engine, its components and sub-components is also described herein. The system(s) and method(s) described herein permit continuous monitoring during the life of the engine for radial clearances and blade and rotor vibration problems, which will assist in correcting and retaining performance for a longer on-wing time in operation. In addition, inconsistent engine-to-engine performance variations due to component tolerances, engine operation characteristics, and operation during extremes in ambient temperatures can be eliminated or significantly minimized when employing the system(s) and method(s) described herein.

Embodiments of a method for manufacturing a turbine engine component are provided, as are embodiments of a thermal growth constraint tool for the manufacture of turbine engine components. In one embodiment, the method includes the steps of obtaining a plurality of arched pieces, arranging the plurality of arched pieces in a ring formation, and bonding the plurality of arched pieces together to produce a monolithic ring by heating the ring formation to a predetermined bonding temperature while constraining the outward radial growth thereof.

An assembly for mounting an igniter in a gas turbine engine combustor between an outer casing and an outer liner, wherein a longitudinal centerline axis extends through the gas turbine engine. The igniter mounting assembly includes a first spring member encircling a portion of said igniter and being positioned between a surface adjacent the outer casing and an outer surface of the outer liner, a first ring member connected to a first end of the first spring member adjacent the outer surface of the outer liner, and a second ring member connected to a second end of the first spring member adjacent the surface adjacent the outer casing. Accordingly, the igniter is able to maintain substantial alignment with respect to an opening in the outer liner while moving radially and/or axially with respect to the outer liner as the outer casing experiences thermal growth greater than the outer liner.

A low-pressure compressor exit stator assembly for a gas turbine includes a multiple of vanes mounted between a full hoop outer shroud and an inner shroud. The outer shroud and inner shroud are mounted to the intermediate case structure. A seal is located between the outer shroud and a bleed duct structure to accommodate thermal growth mismatch.

A vane assembly for a gas turbine is described wherein the vane assembly comprises a first vane and a second vane connected together by a plurality of flanges, at least one fastener, and at least one spring plate. The fastener and hole diameters in the respective flanges are sized such that the first vane and second vane are essentially pinned together along their inner flanges and allowed to adjust due to thermal growth along their outer flanges, while maintaining a constant seal along both inner and outer platform edges. The thermal growth along the outer flanges is made possible by oversized flange holes relative to the diameter of the fastener.

A fuel nozzle assembly is provided. The assembly includes an outer nozzle body having a first end and a second end and at least one inner nozzle tube having a first end and a second end. One of the nozzle body or nozzle tube includes a fuel plenum and a fuel passage extending therefrom, while the other of the nozzle body or nozzle tube includes a fuel injection hole slidably aligned with the fuel passage to form a fuel flow path therebetween at an interface between the body and the tube. The nozzle body and the nozzle tube are fixed against relative movement at the first ends of the nozzle body and nozzle tube, enabling the fuel flow path to close at the interface due to thermal growth after a flame enters the nozzle tube.

A material (100) formed of a sintered aggregation of ceria particles (106), mullite particles (108) and an alumina matrix material (110). Differential thermal expansion of the ceria and mullite particles generates thermal stress sufficient to create micro-cracking of the ceria particles. The ratio of ceria to mullite may be selected to achieve a desired coefficient of thermal expansion for matching the thermal growth of a mating CMC material (102). The micro cracks provide the material with a desired degree of strain tolerance useful in high temperature applications such as a solid core gas turbine vane (20).

A gas turbine engine (40) having an active combustion control system (54) including a sensor element (44) positioned proximate the combustion chamber (46) as part of a sensor assembly (84) including a spring-action bellows (74). The sensor assembly is installed through an opening (69) in the casing (48) of the engine to make contact with the combustor wall (62). The bellows is compressed from its resting position by tightening mounting bolts (70) against a mounting flange (66) of the sensor assembly. The spring action of the bellows ensures contact between the sensing assembly and the combustor wall in spite of differential thermal growth between the casing and the combustor. The sensor element may be replaced by simply removing the mounting bolts without further disassembly of the engine.

A laminate seal assembly, disposed on a stator seal portion and opposite a rotor seal portion of a gas turbine engine comprises a first honeycomb layer having a first edge which engages the rotor portion and a second edge distal from said rotor seal portion, a plurality of honeycomb cells extending between the first edge and the second edge, an intermediate seal plate having a first material surface and a second material surface, the first material surface disposed against the second edge of the first honeycomb layer, a low conductivity structure disposed on the second surface, and a backing plate disposed on against said low conductivity structure, wherein the stator portion may be tuned for thermal growth to match the thermal growth of the rotor portion.

A well liner segment for use in hydrocarbon recovery processes. An elongate, typically cylindrical outer liner member, and an inner elongate liner member concentrically located therewithin is provided. Hydrocarbon upgrading catalyst is provided in the interstitial space between the two members. The outer liner members may be threadably coupled together. A slidable seal is provided between the outer liner and the inner liner to accommodated differential thermal growth between the two liners. A process for use of well liner segments having hydrocarbon upgrader catalyst pre-installed therein, is also provided, as is a method for manufacture of a well liner segment.

A turbine static structure having reduced leakage air is disclosed. A static structure turbine support ring having few segments is disclosed in which the segments have improved thermal expansion capability with reduced air leakage. A plurality of radially extending slots are placed in the segments to reduce stiffness. In order to minimize air leakage through the support ring, generally circumferential slots are placed in the ring and connect with the generally radially extending slots. Positioned in each of the generally radially extending slots and generally circumferential slots, and in contact with each other, are two sheet metal plates. The plates are staked to the support ring structure so as to provide a seal member, yet compensate for thermal growth.

The invention relates to a treatment method of improving oxidation resistance of a thermal barrier coating, belonging to the technical field of thermal barrier coating surface treatment and modification. High current pulse electron beam irradiation is utilized to realize electron beam physical vapor deposition to prepare a yttrium oxide stabilizing zirconium oxide thermal barrier coating to cap ceramic layer columnar crystals, thus the heat-shielding performance and the high temperature oxidation resistance of the coating are improved. The process conditions are shown as follows: the vacuum is 3.5*10<-2>Pa, the voltage is 15kV, the frequency is 1Hz, the pulse width is 120-150ms, the energy density is 10J/cm<2>-20J/cm<2>, the pulse time is 30-40 and the remelting layer thickness reaches at least 10 micrometers. The invention has the advantages that the electron beam physical vapor deposition layer columnar crystals are capped after the high current pulse electron beam irradiation is ended, and thus, the surface of the thermal barrier coating becomes smooth, no penetrable microcracks are generated, the oxygen element diffusion is effectively stopped, the growth of a thermal growth oxidation layer is relieved and the heat-shielding performance and the high temperature oxidation resistance of the thermal barrier coating are obviously improved.

A fuel injector for a gas turbine engine is disclosed which includes an inlet fitting for receiving fuel, a nozzle for issuing fuel into the gas turbine engine, an injector body extending between the inlet fitting and the nozzle and having and interior bore extending therethrough, and an elongated fuel tube disposed within the interior bore of the injector body for delivering fuel from the inlet fitting to the nozzle. The fuel tube has an inlet end portion dynamically associated with the inlet fitting and an outlet end portion rigidly connected to the nozzle. An adapter is operatively associated with either the inlet end section of the fuel tube or a reception bore formed with the inlet fitting of the injector for accommodating a seal member in a manner that permits thermal growth of the injector body relative to the fuel tube.