Rolls-royce Corporation

Edwin Dane

Ian Tibbott

Roderick M Townes

Dougal Richard Jackson

Michiel Kopmels

Caner Hasan Helvaci

Mark Timothy Mitchell

Timothy M Mitchell

Roderick Miles Townes

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.

Cooling arrangements

Cooling arrangements for blades, and in particular turbine blades utilizing gas turbine engines include impingement apertures with impingement jets, which improve cooling efficiency. By providing a leading passage, which is divided at least into a lower section and an upper section, the lower section can have a wall, which is solid for structural integrity while an upper section has impingement apertures for greater cooling efficiency.

Cooling arrangement for utilization with a turbine blade in a gas turbine engine

A rotor blade has a tip with an outer face including at least two channels which each extend to an outlet in the vicinity of the trailing edge. Accordingly, gas leakage around the tip must cross at least three walls, at least in the vicinity of the uncovered turning region near the trailing edge of the blade. Leakage gas entering the channels will tend to create a vortex and pass along the channel to the outlet.

Rotor blades

An aerofoilfor a gas turbine engine includes a root portion, a tip portionlocated radially outwardly of the root portion, leading and trailing edgesextending between the root portionand the tip portionand an internal cooling passage. The aerofoilincludes a plurality of cooling fluid discharge aperturesextending between the root portionand the tip portionin a trailing edge regionto discharge cooling fluid from the internal cooling passageto an outer surfaceof the aerofoil in the trailing edge regionand thereby provide a cooling film in the trailing edge region. The cooling fluid discharge aperturesare arranged so that the flow rate of the cooling fluid discharged from the internal cooling passageto the outer surface trailing edge regionvaries between the root portionand the tip portion

Aerofoils

Cooling with regard to high-pressure turbine platforms is important in order to maintain gas turbine engine efficiency. Cottage Roof dampers located below junction gaps between adjacent platforms have been used but tend to present spent coolant flow at a high angle relative to hot gas flows about the aerofoil blades. The present arrangement has the junction gap angled such that the emergent coolant flow remains adjacent to the suction side to create a coolant film lingering above that suction side of the platform.

Cooling arrangement

An internal fluid cooling system for a gas turbine aerofoil comprises a plurality of multi-pass cooling arrangements each of which consists of a serpentine passage in the interior of the aerofoil. The cooling fluid&#x2014;in particular air&#x2014;is supplied to an inlet end of each passage and exhausted through a multiplicity of discharge holes to provide tip, leading edge, trailing edge and surface film cooling. The inlet end of a first serpentine passage is positioned close to the leading edge and flows rearwards while the inlet end of the second serpentine passage is positioned close to the trailing edge and flows forwards. These serpentine passages are disposed side-by-side, one adjacent the pressure surface and the other adjacent the suction surface on opposite sides of a main load carrying member which comprises a major part of the internal structure of the aerofoil.

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Nottingham, United Kingdom

Edwin Dane