Abstract: A cooling arrangement 21 for use within a gas turbine engine comprises a first shroud or platform 26 incorporating coolant passages 25 and a second shroud or platform 28. Generally, each platform or shroud 26, 28 will incorporate a pressure portion and a suction portion, with the pressure portion incorporating the coolant passages 25 through which the coolant flow 27 becomes incident on a surface 40 of the suction portion of the second shroud 28. The surface 40 is inclined or tapered towards the passage 25, such that there is limited direct impingement upon a front edge 39 of the surface 40. The coolant flow 27 thereby remains adjacent to the surface 40 for a longer period and so enhances cooling efficiency.

Abstract: Cooling within aerofoils (30, 47, 67, 87) is a requirement in order that the materials from which the aerofoil (30, 47, 67, 87) is created can remain within acceptable operational parameters. Traditionally static pressure as well as enhanced dynamic pressure impingement flows have been utilised but there are problems with regard to achieving a necessary over pressure to avoid hot gas ingestion or reduced cooling effect. It will be appreciated that fluid flows and in particular coolant fluid flows must be used most appropriately in order to maintain operational efficiency. By providing a plurality of feed apertures (41, 61, 81) which are shaped to have an entry portion (51, 71, 91) which is generally elliptical and an exit portion (52, 72, 92) it is possible to grab and turn a proportion of a feed flow (44, 64, 84) for substantially perpendicular or other angular presentation to an opposed surface of a cooling chamber (42, 62, 82) within which cooling is required.

Abstract: In order to couple coolant air flow presented through a coolant gallery 4, 24 through an opening 7, 27 into a passage 8, 28 a flow deflector 6, 26 is provided. The flow deflector 6, 26 progressively deflects the coolant air flow 5, 25 through the opening 7, 27 such that there is reduced loss in coolant flow 5, 25 pressure.

Abstract: A cooling arrangement comprises a support (20) for a plurality of blades (22). The support (20) comprises a plurality of blade mounting members (28) provided between adjacent blades (22). The blades (22) are mounted upon the blade mounting members (28). The cooling arrangement defines a pathway (36) for a cooling fluid. The cooling arrangement further includes a fluid directing formation (40, 44, 44A) to direct the cooling fluid across the blade mounting member (28).

Abstract: In order to couple coolant air flow presented through a coolant gallery 4, 24 through an opening 7, 27 into a passage 8, 28 a flow deflector 6, 26 is provided. The flow deflector 6, 26 progressively deflects the coolant air flow 5, 25 through the opening 7, 27 such that there is reduced loss in coolant flow 5, 25 pressure.

Abstract: Turbine blades used in jet engines generally require cooling in order to achieve desired engine performance. Cooling of blade tip areas is difficult due to the limited space available such that thickening tip areas in order to allow passages and holes to be incorporated adds to weight and therefore stressing along with causing additional manufacturing costs. The present cooling arrangement includes coolant release passages 5 which present coolant flow to coolant entrainment elements or fins 2 such that the coolant flow is entrained close to the blade tip surface 12. Thus, turbulent air flow caused by adjacent shrouds and edges are inhibited from diluting the coolant flow and therefore reducing thermal efficiency.

Abstract: Turbine blades used in jet engines generally require cooling in order to achieve desired engine performance. Cooling of blade tip areas is difficult due to the limited space available such that thickening tip areas in order to allow passages and holes to be incorporated adds to weight and therefore stressing along with causing additional manufacturing costs. The present cooling arrangement includes coolant release passages 5 which present coolant flow to coolant entrainment elements or fins 2 such that the coolant flow is entrained close to the blade tip surface 12. Thus, turbulent air flow caused by adjacent shrouds and edges are inhibited from diluting the coolant flow and therefore reducing thermal efficiency.