A filtering chamber for a gas turbine having a combustor, compressor and air inlet duct, and a corresponding maintenance method is described. The filtering chamber includes a first chamber in an inlet plenum; a second chamber in the inlet plenum; and an air bypass mechanism configured to reduce a pressure difference across a final filter that separates the first chamber from the second chamber.

A tubing assembly is provided that can comprise a plurality of tubes or lumens that can be disposed within a head of a peristaltic pump. The tubing assembly can provide a flow rate or volume capacity that is generally equal to or greater than that achieved with a comparable prior art tube while operating at higher pressures than that possible using the prior art tube. Further, in accordance with some embodiments, the tubing assembly can achieve a longer working life than a comparable prior art tube, and the load on the pump motor can be reduced such that the pump life is increased and/or a larger pump motor is not required to achieve such advantageous results.

An electrical raft assembly for a gas turbine engine is provided. The raft assembly comprises a rigid electrical raft formed of a rigid material that includes an electrical system comprising electrical conductors embedded in the rigid material. The raft assembly further comprises an engine component that is mounted to the electrical raft. The electrical raft includes one or more integral cooling passages which guide a coolant fluid through the raft to cool the engine component.

A rigid electrical raft has electrical conductors embedded in a rigid material. The electrical conductors transmit electrical signals through the rigid electrical raft, which may form part of an electrical system of a gas turbine engine. The rigid electrical raft also has electrical heating elements embedded therein. The electrical heating elements provide heat which may be used, for example, to prevent condensation and/or ice build-up and/or to raise the temperature of electrical components to be within a desired range.

A liquid ring pump includes a planar port plate having first and second planar walls, a sidewall which defines a shaft receiving aperture, an inlet, and an outlet. An opening is formed in the port plate and includes an open end that extends through the sidewall and an open face that extends through the first planar wall. A rotor shaft is rotatable about a central axis and is positioned such that a portion of the rotor shaft extends into the shaft receiving aperture. An aperture is formed in the port plate and positioned substantially opposite the opening. The opening, a space defined between the rotor shaft and the sidewall, and the aperture, cooperate to define a channel that extends between a first side of the shaft receiving aperture and a second side of the shaft receiving aperture, wherein the channel is formed entirely coplanar with the port plate.

An electrical raft 200 comprising electrical conductors 252 embedded in a rigid material are provided to a gas turbine engine. The raft 200 is used to transport electrical signals (which may be, for example power and/or control signals) around a gas turbine engine. The electrical raft 200 has an electrical connector 700 embedded therein which is used to connect the electrical raft to an electrical unit, such as an EEC of a gas turbine engine The electrical connector 700 is resiliently biased so as to ensure a reliable electrical connection.

A gas turbine engine 10 comprises at least one rigid raft assembly that has a fluid passageway 210 at least partially embedded therein. The fluid passageway 210 is at least a part of a fluid system. In addition to the fluid passageway 210, the rigid raft assembly 200 also has at least a part of another system. For example, the rigid raft assembly may also include electrical conductors 252, which are part of an electrical system. The rigid raft assembly 200 may be lighter, easier to assemble, more robust and more compact than conventional solutions for providing systems to gas turbine engines.

The present invention provides a gas turbine engine part which has a primary purpose in the engine which is structural and/or aerodynamic. The part is formed of rigid composite material, and has an electrical system comprising electrical conductors permanently embedded in the composite material. This provides advantages in terms of weight, complexity, and build time.

An electrical assembly 600 comprising an electrical raft 200 and an electronic unit 300 is provided to a gas turbine engine 10. The electrical raft 200 has electrical conductors 252 embedded in a rigid material 220, which may be a rigid composite material. The electrical conductors 252 are in electrical contact with the electronic unit 300. When the electronic unit 300 is installed, at least a part 310 of it forms a part of a gas-washed surface of the engine 10. The electronic unit 300 is then easily accessible from the engine 10, and potentially complex and/or heavy access doors/panels may not be required.

An adjustable and lockable turnbuckle may include an elongated body having internal threading within a first end thereof. The turnbuckle may include a first extension rod having external threading configured to mate with the internal threading at the first end of the elongated body. The turnbuckle may include a first jam nut having internal threading and a skirt. The internal threading of the first jam nut may be configured to mate with the external threading of the first extension rod to tighten the first jam nut against the first end of the elongated body so that the skirt of the first jam nut is positionable about the first end of the elongated body. A first aperture may extend through the elongated body, the first extension rod, and the skirt of the first jam nut. Moreover, a first pin may be positioned within the first aperture.