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In a compressor rotor assembly of an axial flow gas turbine engine, wherein the rotor disk has a circumferential blade retaining slot for receiving the root of each blade of a row of blades, a ladder seal is provided between the slot and the blade platforms to limit the leakage of working medium gas

In a compressor rotor assembly of an axial flow gas turbine engine, wherein the rotor disk has a circumferential blade retaining slot for receiving the root of each blade of a row of blades, a ladder seal is provided between the slot and the blade platforms to limit the leakage of working medium gases from the flow path and through the slot. During engine operation, the seal moves radially outwardly into sealing relation with the underside surface of each platform. At the same time, radially inwardly extending flanges of the seal move radially outwardly into sealing relation with the sidewalls of the disk slot.

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A gas turbine engine rotor assembly comprising: (a) an annular rotor disk having a rim and a blade retaining slot extending circmferentially about said rim, said disk having an axis, and said slot having a base and opposed, axially spaced apart sidewalls; (b) a plurality of rotor blades arranged in

A gas turbine engine rotor assembly comprising: (a) an annular rotor disk having a rim and a blade retaining slot extending circmferentially about said rim, said disk having an axis, and said slot having a base and opposed, axially spaced apart sidewalls; (b) a plurality of rotor blades arranged in a circumferential row about said disk rim, each blade having a blade root disposed within said slot and a platform spaced radially outwardly of said root, said platforms of adjacent blades having an axially extending gap therebetween, each platform having a radially inwardly facing underside surface inclined radially outwardly in opposite axial directions away from said root, said underside surface radially spaced from said rim so as to define a circumferentially extending gap therebetween; and (c) an annular ladder seal disposed radially inwardly of said blade platforms and between said platforms and said slot base, said seal having a pair of axially spaced apart, circumferentially extending strips and a plurality of circumferentially spaced apart crossbars extending axially from one strip to the other and integral with both strips, each strip having a circumferential, radially inwardly extending flange axially adjacent to one of said slot sidewalls, wherein said seal is adapted to bend due to centrifugal forces during engine operation such that each of said crossbars contacts said underside surfaces of adjacent blade platforms to seal said gap extending axially between said platforms, and each flange moves radially outwardly as well as axially and contacts its respective slot sidewall to seal said gap extending circumferentially between said rim and said platform underside surfaces.