Patent US3615960A successfully refreshed from Google Patents.
Patent US5100292A successfully refreshed from Google Patents.
US5100292A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Gas turbine engine blade
Assignee: General Electric Co
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Filing: 1990-03-19
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Granted: 1992-03-31
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Expires: 2010-03-19
Abstract
Abstract A gas turbine engine blade is disclosed which includes a dovetail having retention lobes and fillets. Compression loads are provided in the dovetail for introducing compressive prestresses at the fillets for reducing tensile stresses at the fillets due to loads in the blade such as centrifugal tension loads. In an exemplary embodiment, the compression means comprises a cavity in the dovetail and an insert disposed therein in an interference fit for generating compressive stresses at the cavity and at the fillets.
Inventors
- 👤 Lori E. Matula
- 👤 Thomas A. Lindstedt
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-03 21:59
CPC Classifications
F; F01; F01D; F01D5/00; F01D5/30; Y; Y10; Y10S; Y10S416/00; Y10S416/50
Claims Analysis
Total Claims: 13
Claim 1
Independent Claim
112 words
A blade for mounting in a gas turbine engine disk comprising: an airfoil; a dovetail extending from said airfoil and including at least one lobe for retaining said blade in said engine disk, said lobe defining a fillet subject to centrifugal tensile stress upon rotation of said blade in said disk; and compression means disposed in said dovetail for generating compressive stress in said fillet, and including a cavity in said dovetail and an insert disposed in said cavity, said insert being initially sized larger than said cavity so that said insert is disposed in said cavity with an interference fit for generating compressive stresses at said cavity and at said fillet.
Claim 2
Dependent Claim
112 words
A blade for mounting in a gas turbine engine disk comprising: an airfoil; a dovetail extending from said airfoil and including at least one lobe for retaining said blade in said engine disk, said lobe defining a fillet subject to centrifugal tensile stress upon rotation of said blade in said disk; and compression means disposed in said dovetail for generating compressive stress in said fillet, and including a cavity in said dovetail and an insert disposed in said cavity, said insert being initially sized larger than said cavity so that said insert is disposed in said cavity with an interference fit for generating compressive stresses at said cavity and at said fillet.
Claim 3
Dependent Claim
24 words
A blade according to claim 1 wherein said cavity has a substantially rectangular cross section and said insert has a substantially rectangular cross section.
Claim 4
Dependent Claim
58 words
A blade according to claim 2 wherein said dovetail is symmetric and includes a spaced pair of said lobes and fillets, said lobes being joined together at a base of said dovetail, and said cavity is disposed equidistantly between said pair of lobes in said dovetail base, and said compression means effects compressive stress in both said fillets.
Claim 5
Dependent Claim
16 words
A blade according to claim 1 wherein said cavity is cylindrical and said insert is cylindrical.
Claim 6
Dependent Claim
91 words
A blade according to claim 1 wherein: said dovetail includes a shank joining said lobe to said airfoil at said fillet, a longitudinal axis extending through said lobe and said shank, an axial axis disposed perpendicularly to said longitudinal axis, a transverse axis disposed perpendicularly to both said longitudinal axis and said axial axis, said lobe having a peak disposed along a line of maximum width disposed perpendicularly to said longitudinal axis, and a base at said lobe; and said compression means cavity comprises a U-shaped channel extending into said base.
Claim 7
Dependent Claim
82 words
A blade according to claim 5 wherein: said channel includes two transversely spaced flat side surfaces disposed generally parallel to said longitudinal axis and a bottom surface joining said two channel side surfaces; said insert has a generally rectangular cross section including two transversely spaced side surfaces joined by a top surface and a longitudinally spaced bottom surface; and said insert is sized so that said two insert side surfaces are compressed in an interference fit between said two channel side surfaces.
Claim 8
Dependent Claim
32 words
A blade according to claim 6 wherein said dovetail has a thickness along said axial axis, and said cavity and said insert are coextensive and extend for said thickness of said dovetail.
Claim 9
Dependent Claim
18 words
A blade according to claim 7 wherein said insert bottom surface is spaced from said channel bottom surface.
Claim 10
Dependent Claim
39 words
A blade according to claim 6 further including two of said lobes and two of said fillets and wherein said base extends between said two lobes and said channel is disposed in said base equidistantly between said two lobes.
Claim 11
Dependent Claim
24 words
A blade according to claim 1 further including two of said lobes and two of said fillets disposed symmetrically relative to said longitudinal axis.
Claim 12
Dependent Claim
24 words
A blade according to claim 1 further including two of said lobes and two of said fillets disposed asymmetrically relative to said longitudinal axis.
Claim 13
Dependent Claim
27 words
A blade according to claim 11 wherein said compression means cavity is disposed between said two lobes so that compressive stress is generated in both said fillets.
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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) | 1995-03-31 | 1995-09-30 | 1996-03-31 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1999-03-31 | 1999-09-30 | 2000-03-31 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2003-03-31 | 2003-09-30 | 2004-03-31 | $7700.00 | Window Closed / Lapsed |