Rolls-royce Corporation

Lynne H Turner

Ian Tibbott

Peter Ireland

Anthony John Rawlinson

Paul William Ferra

Anthony B Phipps

A component of a turbine stage of a gas turbine engine is provided, the component forming an endwall for the working gas annulus of the stage. The component has one or more internal plena behind the endwall which, in use, contain a flow of cooling air. The component further has a plurality of exhaust holes in the endwall. The holes connect the plena to a gas-washed surface of the endwall such that the cooling air effuses through the holes to form a cooling film over the gas-washed surface. Each exhaust hole has a flow cross-sectional area which is greater at an intermediate position between the entrance of the hole from the respective plenum and the exit of the hole to the gas-washed surface than it is at said exit.

Endwall component for a turbine stage of a gas turbine engine

A shroud segment for a turbine stage of a gas turbine engine forms an endwall for the working gas annulus of the stage. The segment also provides a close clearance to the tips of a row of turbine blades which sweep across the segment. In use a leakage flow of the working gas passes through the clearance gap between the blade tips and the segment. The segment has a plurality of cooling holes and respective air feed passages for the cooling holes. The cooling holes are distributed over that part of the gas-washed surface of the segment which is swept by the blade tips. The cooling holes deliver, in use, cooling air which spreads over the gas-washed surface. The feed passages are configured such that the delivered air opposes the leakage flow of the working gas.

Turbine stage shroud segment

In order to improve cooling of a blade/disccombination, a pre-swirler featureis utilised in order to present coolant air through presentational pathways typically incorporating holesor grooves/slots such that coolant air displaces hotter air leaked past a seal. The swirler featuresare located within stationary housing componentssuch that the coolant air is propelled at substantially the same rotational speed as the discwhilst presentation of the coolant air flow A, C, E is such that hot air displacement is achieved at least adjacent front facesof blade roots

Mounting arrangement for turbine blades

A gas turbine engine turbine section includes a turbine disk () which carries a stage of turbine blades (). The turbine blades () have fir tree roots () which locate in fir tree grooves () in the rim of disk. Some of the projections that form the fir tree roots () of blades () and fir tree grooves () of disk () are truncated so as to define spaces between their truncated surfaces and the roots between adjacent overlapping projections, thus enabling the passing of a cooling air flow therethrough.

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Bristol, United Kingdom

Lynne H Turner