US3598503A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Blade lock
Assignee: RTX Corp
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Filing: 1969-09-19
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Granted: 1971-08-10
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Expires: 1989-09-19
Abstract
Abstract A turbomachine having a rotor assembly construction wherein a deformable blade lock is inserted in the clearance between the blade root and a slot in the periphery of a disc, the blade lock moving under the influence of centrifugal force in such a manner so as to prevent axial movement of the blade root in the disc slot.
Inventors
- 👤 Gerard Muller
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-05 06:38
CPC Classifications
F; F01; F01D; F01D5/00; F01D5/30; F01D5/32; F01D5/323
Claims Analysis
Total Claims: 4
Claim 1
Independent Claim
181 words
A rotor assembly for a turbomachine comprising a disc having root receiving slots extending transversely of the disc at its periphery, and blades having roots corresponding substantially in shape to and engaging in said slots, the base of each blade root being spaced radially from the base of the slot to define clearance therebetween, wherein the improvement comprises; a deformable blade lock comprising a substantially flat resilient strip positioned in said clearance, the flat strip including a hump therein extending between the blade root and disc periphery, the hump being in contact with the blade root at a point offset with respect to the central plane of the disc, and an integral tabs at each end of the flat strip one of said tabs extending radially outward and engaging with the end of the blade root and the other tab extending radially inwardly to overlie the side of the disc thereby to lock the blade root against axial movement in the disc, the contact between the blade root and the hump being offset from the central plane in an upstream direction.
Claim 2
Dependent Claim
181 words
A rotor assembly for a turbomachine comprising a disc having root receiving slots extending transversely of the disc at its periphery, and blades having roots corresponding substantially in shape to and engaging in said slots, the base of each blade root being spaced radially from the base of the slot to define clearance therebetween, wherein the improvement comprises; a deformable blade lock comprising a substantially flat resilient strip positioned in said clearance, the flat strip including a hump therein extending between the blade root and disc periphery, the hump being in contact with the blade root at a point offset with respect to the central plane of the disc, and an integral tabs at each end of the flat strip one of said tabs extending radially outward and engaging with the end of the blade root and the other tab extending radially inwardly to overlie the side of the disc thereby to lock the blade root against axial movement in the disc, the contact between the blade root and the hump being offset from the central plane in an upstream direction.
Claim 3
Dependent Claim
210 words
A rotor construction for a gas turbine engine comprising a disc having root receiving slots extending transversely of the disc at its periphery, and blades having roots corresponding substantially in shape to and engaging in said slots, the base of the blade roots being spaced radially from the slot to define clearance between the blade root and disc periphery, wherein the improvement comprises; a deformable blade lock comprising a substantially flap strip thinner than and positioned in said clearance, the flat strip having an offset therein extending outwardly between the blade root and disc periphery, the offset being in contact with the blade root at a point spaced upstream with respect to the central plane of the disc said strip having a first tab at the upstream end thereof to overlie the side surface of the disc and a second tab at the downstream end thereof to overlie the end of the blade root each tab being connected to the flat strip and being movable in response to centrifugal force, the movement of the downstream tab being greater than the movement of the upstream tab by reason of the greater distance from the contact point between the offset and the blade root about which the strip pivots under centrifugal force.
Claim 4
Dependent Claim
210 words
A rotor construction for a gas turbine engine comprising a disc having root receiving slots extending transversely of the disc at its periphery, and blades having roots corresponding substantially in shape to and engaging in said slots, the base of the blade roots being spaced radially from the slot to define clearance between the blade root and disc periphery, wherein the improvement comprises; a deformable blade lock comprising a substantially flap strip thinner than and positioned in said clearance, the flat strip having an offset therein extending outwardly between the blade root and disc periphery, the offset being in contact with the blade root at a point spaced upstream with respect to the central plane of the disc said strip having a first tab at the upstream end thereof to overlie the side surface of the disc and a second tab at the downstream end thereof to overlie the end of the blade root each tab being connected to the flat strip and being movable in response to centrifugal force, the movement of the downstream tab being greater than the movement of the upstream tab by reason of the greater distance from the contact point between the offset and the blade root about which the strip pivots under centrifugal force.
References Cited (Backward Citations)
No citation records indexed.
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1974-08-09 | 1975-02-08 | 1975-08-10 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1978-08-09 | 1979-02-08 | 1979-08-10 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1982-08-09 | 1983-02-08 | 1983-08-10 | $7700.00 | Window Closed / Lapsed |