Patent ID: 8696304
Filing Date: 2014-04-15
Classification: F01D,Y02T

Abstract:
1. A turbine disk and blade arrangement for a gas turbine engine in which a plurality of turbine blades are mounted circumferentially around a disk, each blade having a fir tree root which provides on circumferentially spaced sides thereof a series of fore-to-aft-extending projections and grooves, and the disk having a plurality of circumferentially spaced, radially extending posts which define fir tree recesses therebetween, each fir tree recess also providing on circumferentially spaced sides thereof a series of fore-to-aft-extending projections and grooves, each fir tree root being slidable into a respective fir tree recess with the projections and grooves on facing sides of the fir tree root and the fir tree recess interengaging with each other; wherein on each pair of facing sides of the fir tree root and the fir tree recess, one or more of the projections of the fir tree roots and/or the fir tree recesses are truncated to form fore-to-aft-extending cooling passages between facing sides of the fir tree roots and fir tree recesses, and the arrangement has lock plates which cover forward surfaces of the posts and of the fir tree roots and/or cover rearward surfaces of the posts and of the fir tree roots, the lock plates and the posts defining feed channels therebetween which feed cooling air to the cooling passages, the feed channels are partitioned such that each cooling passage extends to a respective feed channel.