Abstract: A stationary gas turbine engine includes an axial compressor; a turbine; a stationary inner barrel downstream of the compressor; a brush seal including a ring-shaped holder supported by the inner barrel, and a multiplicity of inwardly extending bristle members having an ambient temperature clearance of not less than 0.015 percent of a rotor land region diameter of the rotor under cold conditions for restricting air passage into the chamber from the compressor. The flow of cooling air from the chamber is preferably alterable by a fluid port extending through one wall of the inner barrel, the fluid port being connected to an auxiliary source of pressure air external of the inner barrel, whereby pressure air from the auxiliary source augments the flow of cooling air from the chamber. A calibrated needle valve can adjustably restrict the flow of auxiliary air for controlling a monitored operating parameter such as the temperature within the chamber.

Abstract: A stationary gas turbine engine includes an axial compressor; a turbine; a stationary inner barrel downstream of the compressor; a brush seal including a ring-shaped holder supported by the inner barrel, and a multiplicity of inwardly extending bristle members having an ambient temperature clearance of not less than 0.015 percent of a rotor land region diameter of the rotor under cold conditions for restricting air passage into the chamber from the compressor. The flow of cooling air from the chamber is preferably alterable by a fluid port extending through one wall of the inner barrel, the fluid port being connected to an auxiliary source of pressure air external of the inner barrel, whereby pressure air from the auxiliary source augments the flow of cooling air from the chamber. A calibrated needle valve can adjustably restrict the flow of auxiliary air for controlling a monitored operating parameter such as the temperature within the chamber.

Abstract: A method and apparatus for monitoring the performance of a turbine by monitoring the temperature in a gap between the inside of a shroud and the tips of the turbine blades as they rotate.

Abstract: A tip shroud rail for a tip shroud of at least one turbine rotor blade, the tip shroud rail comprising a base integrally attached to the tip shroud, a top distally positioned from the base, an upstream surface, and a downstream surface, wherein the tip shroud rail has a height, h, as measured from the base to the top, and a width, w, as measured from the upstream surface to the downstream surface, wherein the width, w, of the tip shroud rail, as measured at the top, is greater than the width, w, of the tip shroud rail, as measured at one-half the height, h/2, of the tip shroud rail.

Abstract: A method and apparatus for monitoring the performance of a turbine by monitoring the temperature in a gap between the inside of a shroud and the tips of the turbine blades as they rotate.

Abstract: An axial flow compressor and a method for mounting the stator blades in the compressor. The compressor is comprised of a stator casing having a rotor axially positioned therein. The casing has internal circumferential grooves into which the stator blades are equally spaced therein. Resilient spacers, e.g. leaf spring, are positioned within any spaces which might exist in the groove after all of the blades have been properly spaced around the groove.

Abstract: An improved turbine blade having a tip configured to provide a reduced blade tip clearance between the blade tip and the inside of a turbine casing and to provide an improved flow path for the discharge of cooling air from the turbine blade tip.

Abstract: Nozzle assembly for injecting a liquid into a process unit through a cross fitting body having at least one of a first and second crossing passageway therethrough with a tubular member carrying a nozzle being injected through one of the cross passageways to position the nozzle carried on the tubular member for the injection of liquid into the processing unit with the liquid being supplied to the tubular member via the other crossing passageway through which liquid is supplied to openings in the tubular member which is in liquid communication with the first crossing passageway to supply liquid to the nozzle.

Abstract: An axial flow compressor and a method for mounting the stator blades in the compressor. The compressor is comprised of a stator casing having a rotor axially positioned therein. The casing has internal circumferential grooves into which the stator blades are equally spaced therein. Resilient spacers, e.g. leaf spring, are positioned within any spaces which might exist in the groove after all of the blades have been properly spaced around the groove.

Abstract: An axially loaded floating brush seal useful in a stationary gas turbine engine having a first rotary compressor component having a rotor having a radial surface, a second non-rotary component having an end ending near the radial surface with the floating brush seal being positioned between the first and the second components to substantially reduce the flow of air between the first and second components. A method for controlling the flow of cooling air into a chamber in the second component using the rotary brush seal is also disclosed.

Abstract: An axial compressor apparatus and a method for reducing the amount of a bearing lubricant passed into the inlet air to the axial compressor by the use of a brush seal between a shaft bearing supporting a shaft axially positioned in the axial compressor and having a rotor downstream relative to air flow through the axial compressor from the brush seal with the brush seal being in contact with the shaft to reduce the passage of the bearing lubricant past the brush seal and into the inlet air.

Abstract: An axially loaded floating brush seal useful in a stationary gas turbine engine having a first rotary compressor component having a rotor having a radial surface, a second non-rotary component having an end ending near the radial surface with the floating brush seal being positioned between the first and the second components to substantially reduce the flow of air between the first and second components. A method for controlling the flow of cooling air into a chamber in the second component using the rotary brush seal is also disclosed.

Abstract: An improved turbine blade having a tip configured to provide a reduced blade tip clearance between the blade tip and the inside of a turbine casing and to provide an improved flow path for the discharge of cooling air from the turbine blade tip.

Abstract: Nozzle assembly for injecting a liquid into a process unit through a cross fitting body having at least one of a first and second crossing passageway therethrough with a tubular member carrying a nozzle being injected through one of the cross passageways to position the nozzle carried on the tubular member for the injection of liquid into the processing unit with the liquid being supplied to the tubular member via the other crossing passageway through which liquid is supplied to openings in the tubular member which is in liquid communication with the first crossing passageway to supply liquid to the nozzle.

Abstract: A multi-stage compressor, including a system for the injection of a cooling liquid into at least a portion of the compressor stages to increase the efficiency of the multi-stage compressor by reducing the temperature of the compressed gas produced in the multi-stage compressor. A cleaning solution may also be injected through nozzles used for the injection of the cooling liquid.

Abstract: A stationary gas turbine engine includes an axial compressor; a turbine; a stationary inner barrel downstream of the compressor; a brush seal including a ring-shaped holder supported by the inner barrel, and a multiplicity of inwardly extending bristle members having an ambient temperature clearance of not less than 0.015 percent of a rotor land region diameter of the rotor under cold conditions for restricting air passage into the chamber from the compressor. The flow of cooling air from the chamber is preferably alterable by a fluid port extending through one wall of the inner barrel, the fluid port being connected to an auxiliary source of pressure air external of the inner barrel, whereby pressure air from the auxiliary source augments the flow of cooling air from the chamber. A calibrated needle valve can adjustably restrict the flow of auxiliary air for controlling a monitored operating parameter such as the temperature within the chamber.