Blade platform seal for ceramic/metal rotor assembly
Patent
·
OSTI ID:864192
- 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
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Related Subjects
/416/
adjacent
adjacent ones
annular
annular flow
assembled
assembly
axially
axially extending
blade
blade platform
blade platforms
blade root
blades
ceramic
ceramic blade
ceramic blades
circumferentially
circumferentially spaced
closely
closely spaced
combination
configured
conform
connected
disc
distribute
dovetail
edge
edge portion
edge portions
engines
expansion
extending
fingers
flexible
flow
form
gaps
gas
gas turbine
including
loading
metal
metal rotor
ones
operating
operating temperature
operating temperatures
operative
passage
platform
platform seal
platforms
plurality
portions
receive
received
retention
rim
root
rotor
rotor assembly
rotor disc
seal
seated
sections
segments
slidably
slidably received
slots
slots therein
spaced
spaced blade
speeds
stressing
surface
temperature
temperature gas
temperatures
therein
thereon
turbine
turbine engine
turbine engines
turbine rotor
underlie
underside
undesirably
unitary
web
adjacent
adjacent ones
annular
annular flow
assembled
assembly
axially
axially extending
blade
blade platform
blade platforms
blade root
blades
ceramic
ceramic blade
ceramic blades
circumferentially
circumferentially spaced
closely
closely spaced
combination
configured
conform
connected
disc
distribute
dovetail
edge
edge portion
edge portions
engines
expansion
extending
fingers
flexible
flow
form
gaps
gas
gas turbine
including
loading
metal
metal rotor
ones
operating
operating temperature
operating temperatures
operative
passage
platform
platform seal
platforms
plurality
portions
receive
received
retention
rim
root
rotor
rotor assembly
rotor disc
seal
seated
sections
segments
slidably
slidably received
slots
slots therein
spaced
spaced blade
speeds
stressing
surface
temperature
temperature gas
temperatures
therein
thereon
turbine
turbine engine
turbine engines
turbine rotor
underlie
underside
undesirably
unitary
web