Abstract: A fluid impingement arrangement comprising a supply manifold and at least one nozzle exit coupled to the supply manifold. The nozzle exit is arranged as a Coanda surface having a restriction and has at least one static pressure tapping that cross-connects two regions of the restriction to induce passive oscillation in a fluid jet passing through the nozzle exit.

Abstract: An elongate fireseal having two ends joined by a longitudinal axis. The fireseal comprises at least two portions having D-shaped cross section and adjacent portions share a common dividing wall. Each end of the fireseal is configured to interlock with a complementary opposite end of the same or a further fireseal.

Abstract: A seal having an integral attachment arrangement. The attachment arrangement comprises at least one attachment feature and at least one locking feature. The at least one attachment feature is configured and arranged to interdigitate with features of another component in a first orientation and to lock to the other component in a second orientation. The second orientation is rotationally displaced from the first orientation.

Abstract: A pipe for carrying a fluid, having a longitudinal axis and defining a radial aperture for release of a jet of fluid having a radial direction component ?, the aperture having an aspect ratio greater than 2 and arranged with its elongate axis within 30 degrees of the longitudinal axis and having area greater than 0.2 the cross-sectional area of the pipe, the fluid jet having an angle ? between 30 and 80 degrees from the longitudinal axis.

Abstract: Breather air, containing oil mist, is discharged from a nacelle 4 of a gas turbine engine through an exhaust port 26 at a surface 22 of the nacelle 4. Energized air, at relatively high velocity is discharged from a clean air outlet 28, and forms a barrier between the breather air and the external surface 22, so preventing contamination of the surface 22 by oil deposited from the breather air.

Abstract: A flow discharge device, such as a bleed assembly in a gas turbine engine, comprises a discharge outlet member having a skirt which is accommodated telescopically in a housing so as to be displaceable with respect to wall of a duct from a retracted position in which slots in the skirt lie outside the duct, and an extended position in which the slots open into the duct for the discharge of a secondary fluid into the flow in the duct. The discharge outlet member is moved to the extended position by the pressure of the secondary fluid acting on a silencer element. A spring returns the discharge outlet member to the retracted position when the flow of the secondary fluid is terminated.

Abstract: There is disclosed an impingement cooling arrangement for a gas turbine engine (6), and an engine provided with such an arrangement. The cooling arrangement comprises at least part of a casing (21) configured to define a flowpath for the passage of hot gases through the engine, and a manifold (22) configured to direct cooling air against an outer surface (23) of the casing for impingement cooling thereof. The arrangement is characterized by said manifold (22) being configured to direct a primary flow of cooling air (65) against a first area (64) of the casing outer surface (23) for impingement cooling of said first area, and to recirculate (66) at least a portion of said primary flow of cooling air after impingement against said first area (64) and to direct at least a portion of the recirculated flow against a second area (67) of the casing outer surface (23) for impingement cooling of said second area (67).

Abstract: A fluid impingement arrangement comprising a supply manifold and at least one nozzle exit coupled to the supply manifold. The nozzle exit is arranged as a Coanda surface having a restriction and has at least one static pressure tapping that cross-connects two regions of the restriction to induce passive oscillation in a fluid jet passing through the nozzle exit.

Abstract: A seal having an integral attachment arrangement. The attachment arrangement comprises at least one attachment feature and at least one locking feature. The at least one attachment feature is configured and arranged to interdigitate with features of another component in a first orientation and to lock to the other component in a second orientation. The second orientation is rotationally displaced from the first orientation.

Abstract: A gas turbine engine including a bypass duct defined by radially outer and inner walls, the radially inner wall defined by acoustic panels. The acoustic panels define the outer wall of a heated fire zone. In conventional engines an insulating blanket is attached to the panels, however, this is heavy and costly. Cooling film means are configured to pass bypass air through and over an internal surface of the panel.

Abstract: An elongate fireseal having two ends joined by a longitudinal axis. The fireseal comprises at least two portions having D-shaped cross section and adjacent portions share a common dividing wall. Each end of the fireseal is configured to interlock with a complementary opposite end of the same or a further fireseal.

Abstract: A flow discharge device, such as a bleed assembly in a gas turbine engine, comprises a discharge outlet member 38 having a skirt 44 which is accommodated telescopically in a housing 36 so as to be displaceable with respect to a wall 27 of a duct 22 from a retracted position (FIG. 2) in which slots 48 in the skirt 44 lie outside the duct 22, and an extended position (FIG. 3) in which the slots 48 open into the duct 22 for the discharge of a secondary fluid into the flow in the duct 22. The discharge outlet member 38 is moved to the extended position by the pressure of the secondary fluid acting on a silencer element 46. A spring 52 returns the discharge outlet member to the retracted position when the flow of the secondary fluid is terminated.

Abstract: Breather air, containing oil mist, is discharged from a nacelle 4 of a gas turbine engine through an exhaust port 26 at a surface 22 of the nacelle 4. Energised air, at relatively high velocity is discharged from a clean air outlet 28, and forms a barrier between the breather air and the external surface 22, so preventing contamination of the surface 22 by oil deposited from the breather air.

Abstract: A temperature measuring arrangement measures the temperature of a fluid passing a component. The arrangement includes a temperature measuring device having a substrate of low thermal capacity that has applied thereto two or more temperature recording media. The device is attached to and spaced apart from the component and is in the fluid flow.

Abstract: There is disclosed an impingement cooling arrangement for a gas turbine engine (6), and an engine provided with such an arrangement. The cooling arrangement comprises at least part of a casing (21) configured to define a flowpath for the passage of hot gases through the engine, and a manifold (22) configured to direct cooling air against an outer surface (23) of the casing for impingement cooling thereof. The arrangement is characterised by said manifold (22) being configured to direct a primary flow of cooling air (65) against is a first area (64) of the casing outer surface (23) for impingement cooling of said first area, and to recirculate (66) at least a portion of said primary flow of cooling air after impingement against said first area (64) and to direct at least a portion of the recirculated flow against a second area (67) of the casing outer surface (23) for impingement cooling of said second area (67).

Abstract: A pipe for carrying a fluid, having a longitudinal axis and defining a radial aperture for release of a jet of fluid having a radial direction component ?, the aperture having an aspect ratio greater than 2 and arranged with its elongate axis within 30 degrees of the longitudinal axis and having area greater than 0.2 the cross-sectional area of the pipe, the fluid jet having an angle ? between 30 and 80 degrees from the longitudinal axis.

Abstract: A temperature measuring arrangement measures the temperature of a fluid passing a component. The arrangement comprises a temperature measuring device having a substrate of low thermal capacity that has applied thereto two or more temperature recording media. The device is attached to and spaced apart from the component and is in the fluid flow.

Abstract: An aircraft electrical component cooling arrangement comprises at least one electrical component (40) housed in a body (38), for example an engine's electronic controller, characterised in that fuel is passed through the body (38) and directly over the component (40). Advantageously, this maintains a uniform temperature of the electronic components, protection against internal and external fire, ability to further miniaturise electrical components and/or combine units due to enhanced cooling effectiveness over convention air cooled systems.

Abstract: A gas turbine engine (10) comprising a bypass duct (22) defined by radially outer and inner walls (27, 30), the radially inner wall (30) defined by acoustic panels (30). The acoustic panels (30) define the outer wall of a heated fire zone. In conventional engines an insulating blanket is attached to the panels, however, this is heavy and costly. The present invention comprises cooling film means (50) to pass bypass air through and over an internal surface (39) of the panel (30).

Abstract: The fire resistance of components normally subject to a standard flame test is evaluated using low temperature model tests. Reynolds number, Froude number, the pressure ratio of the flame to the surrounding atmosphere are matched in the modelling parameters and account is taken of the Prandtl number. Also, the model flow is controlled so as to match the change of momentum flux ratio in the flow through the burner used in a standard flame test. The method allows testing of easily produced model components at temperatures less than 90° C., with savings of cost and time.