Patent US2559168A successfully refreshed from Google Patents.
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US4098559A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Paired blade assembly
Assignee: RTX Corp
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Filing: 1976-07-26
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Granted: 1978-07-04
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Expires: 1996-07-26
Abstract
Abstract A rotor blade system which is adaptd for long term reliable operation in a gas turbine engine is disclosed. Techniques incorporating composite materials into the rotor system are developed. One rotor structure shown utilizes a paired blade assembly having a core of continuous fibers running from the tip of one blade to the tip of the adjacent blade. Each of said paired blade assemblies is mchanically detachable from the engine rotor.
Inventors
- 👤 Jerry Lee Price
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-06 14:36
CPC Classifications
F; F01; F01D; F01D5/00; F01D5/34; F01D5/12; F01D5/22; F01D5/225; F01D5/28; F01D5/282; F01D5/30; F01D5/3053; F01D5/3069; F05; F05D; F05D2300/00; F05D2300/60; F05D2300/603; F05D2300/614
Claims Analysis
Total Claims: 3
Claim 1
Independent Claim
171 words
A rotor assembly for a gas turbine engine, which comprises: a rotor disk having a front plate and a rear plate which are contoured to form an outwardly facing circumferentially extending channel therebetween; and a plurality of unitized blade assemblies mounted in and extending outwardly from said channel, each assembly including a central platform block adapted for mechanical attachment to the rotor disk, a core of continuous fibers having a central portion which extends around said platform block, and having a first end and an opposite end which extend outwardly from said block in essentially the same direction; an outer platform block adapted to hold, in cooperation with the central platform block, the central portion of the core of continuous fibers therebetween; a first shell having an airfoil-shaped contour which encases said first end of the core of continuous fibers to form a first rotor blade; and a second shell having an airfoil-shaped contour which engages said opposite end of the core of continuous fibers to form a second rotor blade.
Claim 2
Dependent Claim
171 words
A rotor assembly for a gas turbine engine, which comprises: a rotor disk having a front plate and a rear plate which are contoured to form an outwardly facing circumferentially extending channel therebetween; and a plurality of unitized blade assemblies mounted in and extending outwardly from said channel, each assembly including a central platform block adapted for mechanical attachment to the rotor disk, a core of continuous fibers having a central portion which extends around said platform block, and having a first end and an opposite end which extend outwardly from said block in essentially the same direction; an outer platform block adapted to hold, in cooperation with the central platform block, the central portion of the core of continuous fibers therebetween; a first shell having an airfoil-shaped contour which encases said first end of the core of continuous fibers to form a first rotor blade; and a second shell having an airfoil-shaped contour which engages said opposite end of the core of continuous fibers to form a second rotor blade.
Claim 3
Dependent Claim
49 words
The invention according to claim 1 which further includes a reinforcing ring of continuous fibers extending circumferentially about the rotor disk of said assembly and adapted to carry a substantial portion of the centrifugally generated hoop stresses imparted to the disk by the blades of the assembly during rotation.
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USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1981-07-03 | 1982-01-02 | 1982-07-04 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1985-07-03 | 1986-01-02 | 1986-07-04 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1989-07-03 | 1990-01-02 | 1990-07-04 | $7700.00 | Window Closed / Lapsed |