US 6,447,250 B1 · Non-integral fan platform

Abstract

A gas turbine engine rotor disk has a number of annular hubs circumscribed about a centerline and each of the hubs is connected to a disk rim by a web. A plurality of circumferentially spaced apart circular arc dovetail slots are disposed through the rim. Circumferentially extending annular burst slots extend radially through the rim into the dovetail slots between each adjacent pair of the webs. The fan blades have circular arc dovetail roots disposed within the circumferentially spaced apart circular arc dovetail slots. A one piece spinner attached to a forward extension of the disk at a location between a tip and an axially aft spinner end of the spinner. Non-integral platforms circumferentially disposed between the fan blades. A booster spool is connected to the rotor disk by a mounting plate therebetween and the platforms are radially retained to the disk and mounting plates by pins through holes in mounting lugs depending radially inwardly from the platforms. Pairs of circumferentially oppositely facing retaining slots have retainers disposed therein which extend across the dovetail slots to axially retain the dovetail roots in the dovetail slots.

Claims24

Dependent claims

A non-integral gas turbine engine fan blade platform for circumferential disposition between fan blades, said platform comprising:

a platform wall with a radially outer surface which faces radially outwardly and a radially inner surface which faces radially inwardly,
said platform wall is sloped with respect to a centerline with an increasing radius of the outer surface in the axially aft direction,
forward, mid, and aft mounting lugs depend radially inwardly from said platform wall, and
a wedge shaped platform bumper depends radially inwardly from the inner surface of the platform wall and is axially located forward of said mid mounting lug.

1 more element

A gas turbine engine rotor assembly comprising:

a disk having a number of annular hubs circumscribed about a centerline,
each of said hubs connected to a disk rim by a web,
a plurality of circumferentially spaced apart circular arc dovetail slots disposed through said rim, extending circumferentially between disk posts, extending axially from a forward end to an aft end of said rim, and extending radially inwardly from a disk outer surface of said rim,
a plurality of fan blades having circular arc dovetail roots disposed in said circular arc dovetail slots,
non-integral gas turbine engine fan blade platforms mounted on said disk and circumferentially disposed between said fan blades,
each of said platforms comprising;
a platform wall with a radially outer surface which faces radially outwardly and a radially inner surface which faces radially inwardly,
said platform wall sloped with respect to a centerline with an increasing radius of the outer surface in the axially aft direction,
forward, mid, and aft mounting lugs depend radially inwardly from said platform wall, and
a wedge shaped platform bumper depends radially inwardly from the inner surface of the platform wall and is axially located forward of said mid mounting lug.

7 more elements

Dependencies are inferred from the claim text.

Non-integral fan platform

Life of this patent

Non-integral fan platform

Life of this patent

Abstract

Claims24