Abstract: A pressure sensing apparatus is provided for sensing gas pressure at a pressure tapping. The apparatus has a pressure sensor which provides a pressure measurement signal in response to the pressure of a gas admitted into the sensor at a gas inlet port thereof. The apparatus further has a gas conduit which extends from the inlet port. An end of the conduit distal from the inlet port is adapted to receive the gas at the pressure tapping. The apparatus further has a condenser on the gas conduit. The condenser contains condensation surfaces on which humidity in the gas flowing from the pressure tapping to the inlet port condenses out. In operation the temperature at the condenser is lower than at the pressure tapping.

Abstract: A pressure sensing apparatus is provided for sensing gas pressure at a pressure tapping. The apparatus has a pressure sensor which provides a pressure measurement signal in response to the pressure of a gas admitted into the sensor at a gas inlet port thereof. The apparatus further has a gas conduit which extends from the inlet port. An end of the conduit distal from the inlet port is adapted to receive the gas at the pressure tapping. The apparatus further has a condenser on the gas conduit. The condenser contains condensation surfaces on which humidity in the gas flowing from the pressure tapping to the inlet port condenses out. In operation the temperature at the condenser is lower than at the pressure tapping.

Abstract: A noise reduction device 40, for example for use in a bleed assembly 30 of a gas turbine engine, comprises partitions 50, 52 forming cells 54 having apertures 56, 58, 60 which provide contractions and sudden expansions of flow passing through the device. The apertures 56, 58, 60 are disposed relative to each other so as to force the flow to change direction within the cells 54 to break up jets of gas issuing from the apertures 56, 58, 60. Webs 62, 64, 66 may be provided adjacent the apertures 56, 58, 60 to direct flow and to assist in generating turbulence.

Abstract: A bleed valve (30) for a gas turbine engine (10) comprises a diffuser (50), through which heated compressor bleed air flows (54) into a bypass duct (22) air stream (B), has a plurality of small holes (40). The plurality of holes (40) is divided into two or more arrays of holes (52p,q,r), each array of holes (52p,q,r) is angled (?) away from one another so that their respective bleed flows (54p,q,r) do not coalesce. This separation improves mixing with the air stream (B) and helps prevent hot bleed air damaging nacelle and other engine components.