Cooling arrangement
Within components such as high pressure turbine blades and aerofoils in a gas turbine engine it is important to provide cooling such that these components remain within acceptable operational parameters. Typically, film cooling as well as convective cooling is utilized. Film cooling requires holes from a feed passage from which the coolant is presented upon an external surface to develop the film. The holes themselves can create cooling through convective cooling effects. In order to maximize the convective cooling effect holes are created which have an indirect path about a direct line between an inlet and an outlet for the hole. By creating an indirect path in the form of a helix or spiral which in turn may have a variable cross sectional area from the inlet to the outlet control of coolant flow can be achieved. The inlet may have a bell mouth shape while the hole may have a slot or elliptical cross section to achieve greater diffusion of the coolant flow in order to create an improved exit blow rate for instant film development.
1. A component for a gas turbine engine,
the component having a wall defining an internal surface, an external surface and a cooling passage,
the cooling passage having an inlet defined in the internal surface, and an outlet defined in the external surface,
the cooling passage defining a helix arranged to flow cooling air from the inlet towards the external surface, then to turn the cooling air towards the internal surface, before turning the cooling air back towards the external surface and through the outlet, wherein
an axis of the helix defines the curvature and torsion of the helix, and the axis is substantially perpendicular to a thickness of the wall,
the inlet to the hole from the cooling passage has a bell end cross section, and
the outlet is in the form of a slot arranged to develop a surface film upon the external surface.
2. The component of claim 1 , wherein the helix is a double helix.
3. The component of claim 1 , wherein the cooling passage extends generally along a direct line between the inlet and the outlet.
4. The component of claim 1 , wherein the direct line is angled to a perpendicular projected radially from the external surface.
5. The component of claim 1 , wherein the cooling passage has a pigtail cross section.
6. The component of claim 1 , wherein the cooling passage is configured at the outlet to project a fluid upon the external surface.
7. The component of claim 6 , wherein the outlet is arranged to project the fluid to develop film cooling upon the external surface.
8. The component of claim 1 , wherein the cooling passage has a variable cross sectional area between the inlet and the outlet.
9. The component of claim 8 , wherein the cooling passage tapers in cross section between the inlet and the outlet.
10. The component of claim 1 , wherein a cooling air flow path at least in part is defined by a shape of the cooling passage.
11. The component of claim 1 , wherein a cooling flow path at least in part is defined by surface features of a wall of the cooling passage.
12. The component of claim 1 , wherein the cooling passage is angled at the outlet.
13. The component of claim 1 , wherein the component is an aerofoil utilised in a rotor or a guide vane in a gas turbine engine.
14. The component of claim 1 , wherein the cooling passage is a feed passage for coolant through the component.
15. The component of claim 1 , wherein the cooling passage has one of an elliptical cross section and a slot cross section.
16. The component of claim 1 , wherein the cooling passage creates one of a clockwise and a counterclockwise pathway from the inlet to the outlet.
17. A plurality of cooling arrangements comprising the component of claim 1 .