Patent US5044885A successfully refreshed from Google Patents.
US5044885A
Expired / Lapsed
US
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Mobile blade for gas turbine engines providing compensation for bending moments
Assignee: Safran Aircraft Engines SAS
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Filing: 1990-03-01
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Granted: 1991-09-03
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Expires: 2010-03-01
Abstract
Abstract In a mobile blade of a gas turbine engine comprising a root, a platform, and a vane forming the aerodynamic portion of the blade, the vane is arranged so that the geometric locus of the centers of gravity of successive cross-sections of the vane between the platform and the tip of the blade vane is a curve including at least one straight line portion which is offset relative to a radial straight line contained in the axial plane of symmetry of the blade root and which is joined progressively to the origin where the radial straight line intersects the junction of the vane with the platform and root of the blade. In the case of a blade with an intermediate shoulder or fin on the vane, the locus of the centers of gravity of the vane cross-sections includes a second straight line portion offset relative to the first straight line portion and connecting assembly therewith in the region of the fin.
Inventors
- 👤 Christian Odoul
- 👤 Marc G. F. Paty
- 👤 Jean-Pierre R. Serey
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-08 05:34
CPC Classifications
F; F01; F01D; F01D5/00; F01D5/12; F01D5/14; F01D5/141; F01D5/22
Claims Analysis
Total Claims: 3
Claim 1
Independent Claim
190 words
A mobile blade for a gas turbine engine having an axis of rotation, which comprises: a root, a platform, and a vane forming the aerodynamic portion of said blade, said vane having a junction portion which merges smoothly with said platform and said root, wherein said vane is arranged such that the geometric locus of the centers of gravity of successive cross-sections of said vane between said platform and the tip of said vane is a curve which has its origin in an axial plane of symmetry of said root at the point where a radial straight line passing through said axis of rotation of said engine meets said junction portion of said root and platform with said vane, and which merges progressively from said origin into a first straight line portion of said curve parallel to said radial straight line and tangentially displaced therefrom in such a manner that the corresponding vane sections are offset overall so as to nullify bending moments at said root by a compensating effect and wherein the radial straight line meets the junction portion at the center of one of the platform and root.
Claim 2
Dependent Claim
190 words
A mobile blade for a gas turbine engine having an axis of rotation, which comprises: a root, a platform, and a vane forming the aerodynamic portion of said blade, said vane having a junction portion which merges smoothly with said platform and said root, wherein said vane is arranged such that the geometric locus of the centers of gravity of successive cross-sections of said vane between said platform and the tip of said vane is a curve which has its origin in an axial plane of symmetry of said root at the point where a radial straight line passing through said axis of rotation of said engine meets said junction portion of said root and platform with said vane, and which merges progressively from said origin into a first straight line portion of said curve parallel to said radial straight line and tangentially displaced therefrom in such a manner that the corresponding vane sections are offset overall so as to nullify bending moments at said root by a compensating effect and wherein the radial straight line meets the junction portion at the center of one of the platform and root.
Claim 3
Dependent Claim
102 words
A mobile blade according to claim 1 wherein said vane carries intermediate fins, and said curve representing the geometric locus of the centers of gravity of successive cross-sections of said vane has, in the region of said fins, a continuous junction part leading to a second straight line portion situated between said fins and said tip of said vane and tangentially displaced from said first straight line portion in such a manner that the corresponding vane sections are offset overall so as to correct for the effect of said fins and nullify the bending moments at said root by said compensating effect.
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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) | 1994-09-02 | 1995-03-04 | 1995-09-03 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1998-09-02 | 1999-03-04 | 1999-09-03 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2002-09-02 | 2003-03-04 | 2003-09-03 | $7700.00 | Window Closed / Lapsed |