Blade platform seal for ceramic/metal rotor assembly

Patent · Fri Jan 01 00:00:00 EST 1982

OSTI ID:864192

Wertz, John L ^[1]

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1. Indianapolis, IN

A combination ceramic and metal turbine rotor for use in high temperature gas turbine engines includes a metal rotor disc having a rim with a plurality of circumferentially spaced blade root retention slots therein to receive a plurality of ceramic blades, each including side platform segments thereon and a dovetail configured root slidably received in one of the slots. Adjacent ones of the platform segments including edge portions thereon closely spaced when the blades are assembled to form expansion gaps in an annular flow surface for gas passage through the blades and wherein the assembly further includes a plurality of unitary seal members on the rotor connected to its rim and each including a plurality of spaced, axially extending, flexible fingers that underlie and conform to the edge portions of the platform segments and which are operative at turbine operating temperatures and speeds to distribute loading on the platform segments as the fingers are seated against the underside of the blade platforms to seal the gaps without undesirably stressing thin web ceramic sections of the platform.

• Assignee: General Motors Corporation (Detroit, MI)
• Patent Number(s): US 4326835
• OSTI ID: 864192
• Country of Publication: United States
• Language: English

Related Subjects

blade
platform
seal
ceramic
metal
rotor
assembly
combination
turbine
temperature
gas
engines
disc
rim
plurality
circumferentially
spaced
root
retention
slots
therein
receive
blades
including
segments
thereon
dovetail
configured
slidably
received
adjacent
ones
edge
portions
closely
assembled
form
expansion
gaps
annular
flow
surface
passage
unitary
connected
axially
extending
flexible
fingers
underlie
conform
operative
operating
temperatures
speeds
distribute
loading
seated
underside
platforms
undesirably
stressing
web
sections
slidably received
edge portions
adjacent ones
turbine rotor
temperature gas
circumferentially spaced
rotor assembly
turbine engine
gas turbine
operating temperature
closely spaced
operating temperatures
turbine engines
edge portion
annular flow
ceramic blade
axially extending
rotor disc
ceramic blades
slots therein
metal rotor
spaced blade
platform seal
blade platform
blade platforms
blade root
/416/