Abstract

A gas turbine reheat system is provided with channel-shaped gutters, with a wall portion spaced from each gutter to form a space therebetween. The space is supplied with cooling air conveniently from the engine by-pass duct.

IPC Classes  ?

• F02K 3/10 - Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluidControl thereof by after-burners
• F02K 1/38 - Introducing air inside the jet
• F02K 1/46 - Nozzles having means for adding air to the jet or for augmenting the mixing region between the jet and the ambient air, e.g. for silencing

Abstract

In a by-pass gas turbine engine having a lobed type by-pass air and turbine exhaust mixer unit, the reheat gutters are arranged in the mixer in the turbine exhaust duct. The gutters extend radially and are substantially Y-shaped, each of the two legs of the Y extending radially along the sides of a mixer lobe.

IPC Classes  ?

• F02K 3/10 - Plants including a gas turbine driving a compressor or a ducted fan with supplementary heating of the working fluidControl thereof by after-burners
• F02K 1/38 - Introducing air inside the jet
• F02K 1/46 - Nozzles having means for adding air to the jet or for augmenting the mixing region between the jet and the ambient air, e.g. for silencing

Abstract

Elbow nozzles in VTOL aircraft engines, are highly stressed when operating, in that they act as high pressure vessels. The invention provides a means for varying the outlet area of such a nozzle without weakening its structure. A single flap is inserted inside the nozzle and connected to the nozzle extremity for pivoting about an axis which lies across the outlet between a position wherein its edges seal against the nozzle side and so restrict the nozzle outlet area and, a position wherein it lies parallel with a wall of the nozzle so that exhaust gas can pass both sides and out of a bigger outlet.

IPC Classes  ?

• B63H 11/10 - Marine propulsion by water jets the propulsive medium being ambient water having means for deflecting jet or influencing cross-section thereof
• B64C 15/00 - Attitude, flight direction or altitude control by jet reaction

Abstract

A nozzle guide vane for a gas turbine engine comprises a hollow ceramic vane member which includes an aerofoil portion and ceramic platforms. The ceramic vane member is supported by engagement of its interior surface with external supporting surfaces on a metallic load-bearing spine adapted to be supported from fixed structure of the engine.

IPC Classes  ?

• F03B 11/00 - Parts or details not provided for in, or of interest apart from, groups