Patent ID: 8419366
Filing Date: 2013-04-16
Classification: F01D,Y02T

Abstract:
1. A blade for a gas turbine engine, the gas turbine engine having axial and radial directions associated therewith, the blade comprising: a leading passage and a feed passage extending side by side along the blade; a wall between the leading passage and the feed passage; a divider wall, the leading passage divided into a lower section and an upper section by the divider wall; film developing apertures incorporated in the lower section of the leading passage; and impingement apertures defined by the feed passage and extending only into the upper section of the leading passage through the wall, whilst the wall along the lower section is solid, wherein the lower section is arranged to receive a radial coolant such that film cooling is developed upon exterior surfaces of the blade through the film apertures, in use, the upper section is arranged to receive coolant from the feeding passage through the impingement apertures, the flow of radial coolant into the lower section is separate from the flow of coolant into the feeding passage, and a relative proportion of the lower section and the upper section of the leading passage provides, in use, a pressure differential in a fluid flow in the feed passage for impingement projection through the impingement apertures, whilst the lower section through the solid wall maintains structural integrity for said blade.