A bleed valve system for a gas turbine engine that includes a retaining ring and a metering ring. The retaining ring abuts an end of a bleed air duct and defines a plurality of retaining ring apertures. The metering ring that is at least partially disposed within the bleed air duct and abuts the retaining ring, the metering ring defining a plurality of metering ring apertures, the metering ring being rotatable relative to the retaining ring to selectively facilitate a fluid flow through the bleed air duct.

A turbine engine includes a compressor section including a compressor, the compressor including an axial compressor stage, a variable outlet guide vane, and a centrifugal compressor stage, the variable outlet guide vane positioned between the axial compressor stage and the centrifugal compressor stage; a bleed assembly including a bleed airflow duct in airflow communication with the compressor and a bleed valve operable with the bleed airflow duct, the bleed valve including a bleed valve actuator; and a linkage assembly coupling the bleed valve actuator with the variable outlet guide vane such that that variable outlet guide vane is moveable with the bleed valve.

Apparatus for selective delivery of pressurised gas comprises a containment wall which at least partially bounds of a volume of pressurised gas during use of the apparatus, and a valve directly coupled to an output port of the containment wall such that the containment wall and the valve retain the pressurised gas when the valve is closed. The apparatus obviates the need for a duct coupling the output port to the input of the valve, and hence reduces the number of interfaces between the output port and the input of the valve from two, as in arrangements of the prior art, to one. The apparatus presents fewer failures modes compared to the case where a duct couples the output port to the valve.

A gas turbine engine comprising: a compressor; a first turbine; and a first compressor bleed valve in fluid communication with the compressor and configured to release bleed air from the compressor; wherein the first compressor bleed valve is configured to release bleed air to a downstream location in the engine, the downstream location being downstream of the first turbine; wherein the first compressor bleed valve is configured to open wherein the first compressor bleed valve is configured to open to at least two positions, to thereby release a variable amount of bleed air from the compressor.

A single-piece gas turbine engine bleed duct for a gas turbine engine including: a main airflow conduit configured to transmit a bleed flow to a location outside the gas turbine engine; a pressure regulating valve for regulating airflow through the main airflow conduit; a first inlet duct for directing airflow to the main airflow conduit and toward the pressure regulating valve, the first inlet duct including a non-return valve; and a second inlet duct for directing airflow to the main airflow conduit and toward the pressure regulating valve, the second inlet duct including a control valve; wherein each of the first and second inlet ducts are directly connectable to an engine casing of a gas turbine engine.

A gas turbine includes a compressor, a combustor, a turbine, a generator, and a control apparatus, the compressor being provided with an air extraction valves, a plurality of inlet guide vanes, and a plurality of casing air extraction valves at its last stage, in which the control is carried out on at least one of the opening of the air extraction valve, the opening of the inlet guide vanes, and the number of openings of the casing air extraction valves which are defined as control parameters taking blade vibration stress values as indexes based on a compressor metal temperature included in behavior parameters of the gas turbine.

A system for bleeding air from a core flow path of a gas turbine engine is disclosed. In various embodiments, the system includes a bleed valve having a bleed valve inlet configured to receive a bleed air from a first access point to the core flow path and a bleed valve outlet; and an air motor having a first air motor inlet configured to receive the bleed air from the bleed valve outlet and a first air motor outlet configured to exhaust the bleed air, the air motor configured to pump the bleed air from the core flow path of the gas turbine engine.

A compressor for use in a gas turbine engine comprises a compressor rotor including blades and a disc, with a bore defined radially inwardly of the disc. A radially outer housing surrounds an outer diameter of the blades. A lower pressure tap and a higher pressure tap tap air from two distinct locations within the compressor and radially outwardly through the outer housing. A valve selectively delivers at least one of the lower pressure tap and the higher pressure tap to the bore of the disc. A control for the valve is programmed to move the valve to a position delivering the higher pressure tap at a point prior to take-off when the compressor is mounted in a gas turbine engine on an aircraft. A gas turbine engine and a method of operating a gas turbine engine are also disclosed.

An inlet pressure valve regulation system to provide a regulated fluid flow includes a housing, first piston assembly, regulating valve, and inlet pressure conduit. The housing has an inlet at an inlet end which receives a pressurized fluid and an outlet at an outlet end which provides the regulated fluid flow. The piston assembly is arranged in the housing and has a first cavity and a control orifice to fluidly connect the inlet to the first cavity. The first piston assembly is configured to regulate the fluid flow. The regulating valve has a first valve chamber, a second valve chamber fluidly connected to a vent, a floating valve seat disposed between the first valve chamber and the second valve chamber, and a valve component. The floating valve seat includes a diaphragm and a seat having a passageway to fluidly connect the first valve chamber and the second valve chamber.

A multi-stage pump featuring first and second stages, each stage having an impeller arranged on a rotor of the pump, each impeller having a hub-side and an eye-side, and each impeller configured to pump a liquid through the pump that applies an axial thrust load caused by a pressure difference in an axial direction from the hub-side to the eye-side of each impeller; and a first and second stage pump casing, each casing configured to form a casing enclosure to contain components of the first stage and the second stage, including each impeller, and configured with one or more pump casing openings formed therein and passing thru the pump casing to leak at least some liquid being pumped from inside to outside the casing enclosure to reduce substantially the axial thrust load caused by the pressure difference in the axial direction from the hub-side to the eye-side of each impeller.