Abstract:
A method of forming an interstage seal including removing a diaphragm seal box (14) from a gas turbine compressor assembly (10) and removing a labyrinth sealing member (12) from the diaphragm seal box (14). An abradable material layer (34) may be deposited on the diaphragm seal box (14). A spray gun may be mounted in relation to an engine disk (16) of the gas turbine compressor assembly (10) for cold-spraying a quantity of particles toward the engine disk (16). The particles may be sprayed at a velocity sufficiently high to cause at least a portion of the quantity of particles to adhere to the engine disk (16). The spray gun may be controlled to deposit a quantity of particles on the compressor disk (16) to form a geometry (32) that will abrade the abradable material layer (34) during operation of the gas turbine compressor assembly (10). The geometry (32) abrading the abradable material layer (34) forms an interstage seal. Rotation of the engine disk (16) within the gas turbine compressor assembly (10) may be controlled during the step of controlling the spray gun. The diaphragm seal box (14) may be reinstalled within the gas turbine compressor assembly (10) so that the geometry (32) aligns with the abradable material layer (34).
Abstract:
A thermal barrier coating including a two layered ceramic barrier coating, an inner ceramic layer and an outer ceramic layer, is provided. The thermal barrier coating has different thicknesses on different places of the component. In addition, the thickness of the inner ceramic layer and the thickness of the outer ceramic layer vary in relation to one another.
Abstract:
A telemetry system for use in a combustion turbine engine (10) that includes a first sensor (306) in connection with a turbine blade (301) or vane (22). A first telemetry transmitter circuit (312) is affixed to the turbine blade and routes electronic data signals, indicative of a condition of the blade, from the sensor to a rotating data antenna (314) that is affixed to the turbine blade or is on a same substrate as that of the circuit. A stationary data antenna (333) may be affixed to a stationary component (323) proximate and in spaced relation to the rotating data antenna for receiving electronic data signals from the rotating data antenna. A second sensor (335) transmits electronic data signals indicative of the stationary component to a second telemetry circuit (332), which routes the signals to the stationary antenna. The stationary antenna transmits the electronic data signals to a receiver (338).
Abstract:
The present invention relates to a non-aqueous coating composition comprising: 1) 75 to 99 wt. %, preferably 85 to 95 wt. % of a hard urethane(meth)acrylate polymer or oligomer; and 2) 1 to 25 wt. %, preferably 5 to 15 wt. % of a soft unsaturated urethane(meth)acrylate polymer or oligomer containing allophanate groups.
Abstract:
In a telemetry system for use in an engine, a circuit structure (34) affixed to a moving part (20) of the engine is disposed for amplifying information sensed about a condition of the part and transmitting the sensed information to a receiver external to the engine. The circuit structure is adapted for the high temperature environment of the engine and includes a differential amplifier (102, 111) having an input for receiving a signal from a sensor (101, 110) disposed on the part. A voltage controlled oscillator (104, 115) with an input coupled to the output of the amplifier produces an oscillatory signal having a frequency representative of the sensed condition. A buffer (105, 116) with an input coupled to the output of the oscillator buffers the oscillatory signal, which is then coupled to an antenna (26) for transmitting the information to the receiver.
Abstract:
A telemetry system for use in a combustion turbine engine (10) having a compressor (12), a combustor and a turbine (16) that includes a sensor (50, 74) in connection with a turbine blade (18) or vane (22). A telemetry transmitter circuit (210) may be affixed to the turbine blade (18) with a first connecting material (52, 152) deposited on the turbine blade (18) for routing electronic data signals from the sensor (50, 74) to the telemetry transmitter circuit (210), the electronic data signals indicative of a condition of the turbine blade (18). An induction power system for powering the telemetry transmitter circuit (210) may include a rotating data antenna (202) affixed to the turbine blade (18) with a second connecting material (140) deposited on the turbine blade (18) for routing electronic data signals from the telemetry transmitter circuit (210) to the rotating data antenna (202). A stationary data antenna (184) may be affixed to a static seal segment 180 adjacent the turbine blade (18) for receiving electronic data signals from the rotating data antenna (202).
Abstract:
Aqueous polyurethane coating compositions are disclosed in this specification. The aqueous polyurethane coating compositions contain a polycarbonate-polyurethane resin component, an aminoplast resin component, and a polyester polyol component.
Abstract:
A method of forming a thermocouple (12), including: depositing a first material on a component (10) to form a first leg (14); depositing a second material through a mask (30) to form a pattern (50) on the component (10), the pattern (50) forming a plurality of discrete second leg junction ends (20) and a continuous patch (52) of the second material comprising indiscrete lead ends of the second legs (16), each second leg junction end (20) spanning from a respective junction (18) with the first leg (14) to the continuous patch (52); and laser-ablating the continuous patch (52) to form discrete lead ends (22) of the second legs (16), each lead end (22) electrically connected to a respective junction end (20), thereby forming discrete second legs (16).
Abstract:
The invention relates to a method for electrical discharge machining of electrically non-conductive material in which a layer of an electrically conductive substance is applied as an auxiliary electrode on the electrically non-conductive material. Said method is characterized in that the electrically conductive substance is chemically converted by oxidative heat treatment after electrical discharge machining.
Abstract:
A telemetry system for use in a combustion turbine engine (10) having a compressor (12), a combustor and a turbine (16) and includes a sensor (118) in connection with a turbine blade (111) or vane (23). A transmitter assembly (117) includes a telemetry transmitter circuit/transceiver may be affixed on a turbine blade (111) or seal plate (115) proximate the turbine blade with a first connecting material (119) deposited on the turbine blade (111) for routing electronic data signals, indicative of a condition of the turbine blade (111), from the sensor (118) to the telemetry transmitter circuit/transceiver. An induction power system for powering the telemetry transmitter circuit/transceiver may include a rotating data antenna (116) affixed to the seal plate (115) with an electrical connection (122) between the telemetry transmitting circuit/transceiver for routing electronic data signals from the telemetry transmitter circuit/transceiver to the rotating data antenna (119).