Abstract: A brush seal for sealing a leakage gap in an axial flow path between a relatively higher fluid pressure region and a relatively lower fluid pressure region. The brush seal may comprise an outer housing and an inner housing located at least partially within and configured for radial displacement relative to the outer housing. The outer housing may comprise a first downstream outer contact member comprising a first upstream facing outer contact surface configured along a first radial contact line. The outer housing may comprise a second downstream outer contact member comprising a second upstream facing outer contact surface configured, and radially spaced from the first upstream facing outer contact surface, along the first radial contact line to define a downstream outer chamber opening of a downstream outer housing chamber therebetween.

Abstract: A sealing arrangement (30) for providing sealing between a first structure (10), e.g. a rotor shaft, and a second structure (15), e.g. a portion of a casing, of an engine, and between first (HP) and second (LP) pressure regions located between the first (10) and second (15) structures, the first pressure region (HP) being at a relatively higher pressure than the second pressure region (LP), and the first structure (10) being moveable relative to the second structure (15) along an axis, wherein the sealing arrangement (30) comprises: a sealing member (20), e.g.

Abstract: An impingement cooling arrangement comprises a projection extending partially across a coolant passage upstream of a jet aperture. An end surface of the projection increases the available surface area for heat exchange with a cross flow whilst a coolant air flow jetted from the jet aperture can transgress a proportion of the air flow passing between the end surface and a junction surface incorporating the jet aperture. A spacing gap B between the end surface and the junction surface avoids localised distortions to the cross flow whilst the projection provides that the coolant air flow projected from the jet aperture mostly passes through a lower turbulence wake downstream of the projection for greater impingement upon a target surface for heat transfer and cooling efficiency. Typically the impingement cooling arrangement is incorporated within turbine blades or vanes of a jet engine.