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US 8,523,523 B2Granted
Cooling arrangements
AssigneeROLLS-ROYCE plc
InventorsRoderick M. Townes, Ian Tibbott, Edwin Dane, Caner H. Helvaci
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AssigneeROLLS-ROYCE plc
InventorsRoderick M. Townes, Ian Tibbott, Edwin Dane, Caner H. Helvaci
Estimating the term…
Providing cooling within hollow blades such as high pressure turbine blades in a gas turbine engine is important to maintain these components within operational margins for the materials from which they are formed. Traditionally, coolant flows in hollow passages have been used along with impingement apertures towards a leading passage for cooling effectiveness. It is known that opposed undulations or ribs can create rotational vortices within the passage. By shaping shaped portions between the opposed undulations and possibly providing undulations upon these shaped portions themselves it is possible to generate stronger more powerful vortices within the passage. These vortices are coupled with the impingement orifices to create proportionally greater impingement jet flow and pressure and therefore cooling effectiveness within the leading passage.
An aerofoil of a gas turbine engine having a rotational axis, the aerofoil comprising an internal passage for a cooling fluid, the passage is partly formed by first and second opposing walls wherein the first wall, comprises at least two apertures, the second wall comprises angled wall portions forming a tip region adjacent the first wall, the passage comprises ribs which together with the wall portions create at least two vortices in the coolant fluid adjacent the apertures to increase the dynamic head of cooling fluid through the apertures, and the apertures are arranged either side of the tip region and into each of which one of the vortices passes coolant fluid with an increased dynamic head.
Dependencies are inferred from the claim text.