US4626461A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Gas turbine engine and composite parts
Assignee: RTX Corp
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Filing: 1983-01-18
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Granted: 1986-12-02
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Expires: 2003-01-18
Abstract
Abstract High strength, fracture tough, high temperature oxidatively stable, gas turbine engine core engine components are described made of silicon carbide fiber reinforced ceramic matrix or silicon carbide fiber reinforced glass matrix material. A gas turbine engine containing core engine components as above described is also disclosed.
Inventors
- 👤 Karl M. Prewo
- 👤 John J. Brennan
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-30 04:34
CPC Classifications
F; F01; F01D; F01D25/00; F01D25/005; B; B32; B32B; B32B18/00; C; C03; C03C; C03C14/00; C03C14/002; C04; C04B; C04B35/00; C04B35/01; C04B35/16; C04B35/18; C04B35/19; C04B35/195; C04B35/622; C04B35/64; C04B35/645; C04B35/71; C04B35/78; C04B35/80; F01D5/00; F01D5/12; F01D5/28; F01D5/282; F01D5/284; F23; F23R; F23R3/00; F23R3/007; C03C2214/00; C03C2214/02; C03C2214/20; C04B2235/00; C04B2235/02; C04B2235/30; C04B2235/32; C04B2235/3201; C04B2235/3203; C04B2235/3205; C04B2235/3206; C04B2235/36; C04B2235/50; C04B2235/52; C04B2235/5208; C04B2235/5216; C04B2235/524; C04B2235/5244; C04B2235/5264; C04B2235/5268; C04B2235/70; C04B2235/72; C04B2235/96; C04B2235/9607; C04B2235/9623; C04B2235/9669; C04B2235/9684; C04B2237/00; C04B2237/30; C04B2237/32; C04B2237/34; C04B2237/341; C04B2237/38; F05; F05D; F05D2220/00; F05D2220/30; F05D2220/32; Y; Y02; Y02T; Y02T50/00; Y02T50/60; Y10; Y10T; Y10T428/00; Y10T428/24; Y10T428/24058; Y10T428/24124; Y10T428/24132
Claims Analysis
Total Claims: 11
Claim 1
Independent Claim
93 words
A gas turbine engine core engine component selected from blades, vanes, discs, side plates, seals, combustor liners, flaps, burner case structures or turbine case structures; comprising a plurality of substantially titanium-free ceramic layers selected from (a) aluminosilicate, (b) lithium aluminosilicate, (c) magnesium aluminosilicate, or (d) mixtures thereof, each layer reinforced with a plurality of unidirectional, continuous length silicon carbide fibers, each layer having an axial flexural strength exemplified by a critical stress intensity factor greater than 10×10 3 psi (inch) 1/2 , high temperature strength, high temperature oxidation stability, and good insulating properties.
Claim 2
Dependent Claim
93 words
A gas turbine engine core engine component selected from blades, vanes, discs, side plates, seals, combustor liners, flaps, burner case structures or turbine case structures; comprising a plurality of substantially titanium-free ceramic layers selected from (a) aluminosilicate, (b) lithium aluminosilicate, (c) magnesium aluminosilicate, or (d) mixtures thereof, each layer reinforced with a plurality of unidirectional, continuous length silicon carbide fibers, each layer having an axial flexural strength exemplified by a critical stress intensity factor greater than 10×10 3 psi (inch) 1/2 , high temperature strength, high temperature oxidation stability, and good insulating properties.
Claim 3
Dependent Claim
15 words
The component of claim 1 wherein the silicon carbide fiber containing layers are uniaxially oriented.
Claim 4
Dependent Claim
15 words
The component of claim 1 wherein the silicon carbide fiber containing layers are multiaxially oriented.
Claim 5
Dependent Claim
16 words
The component of claim 3 wherein the fibers are oriented to 0°/90°, 0°/±45°/90°, or 0°/30°/60°/90° orientation.
Claim 6
Dependent Claim
26 words
The component of claim 1 wherein the silicon carbide fibers comprise a multifilament silicon carbide yarn with an average filament diameter of up to 50 microns.
Claim 7
Dependent Claim
16 words
The component of claim 5 wherein the yarn has an average filament diameter of 5-15 microns.
Claim 8
Dependent Claim
22 words
The component of claim 1 wherein the silicon carbide fibers are present in an amount of at least about 40% by volume.
Claim 9
Dependent Claim
35 words
The component of claim 1 wherein the composite is formed by starting with the ceramic in the glassy state and converting it from the glassy state to the ceramic state after densification of the composite.
Claim 10
Dependent Claim
109 words
A gas turbine engine containing at least one core engine component selected from blades, vanes, discs, side plates, seals, combustor liners, flaps, burner case sturctures or turbine case structures, comprising a plurality of substantially titanium-free ceramic layers selected from the group consisting of (a) aluminosilicate, (b) lithium aluminosilicate, (c) magnesium aluminosilicate, or (d) mixtures thereof, each layer reinforced with a plurality of unidirectional, continuous length silicon carbide fibers, each layer having an axial flexural strength greater than 70,000 psi, a high fracture toughness exemplified by a critical stress intensity factor greater than 10×10 3 psi (inch) 1/2 , high temperature strength, high temperature oxidation stability, and good insulating properties.
Claim 11
Dependent Claim
109 words
A gas turbine engine containing at least one core engine component selected from blades, vanes, discs, side plates, seals, combustor liners, flaps, burner case sturctures or turbine case structures, comprising a plurality of substantially titanium-free ceramic layers selected from the group consisting of (a) aluminosilicate, (b) lithium aluminosilicate, (c) magnesium aluminosilicate, or (d) mixtures thereof, each layer reinforced with a plurality of unidirectional, continuous length silicon carbide fibers, each layer having an axial flexural strength greater than 70,000 psi, a high fracture toughness exemplified by a critical stress intensity factor greater than 10×10 3 psi (inch) 1/2 , high temperature strength, high temperature oxidation stability, and good insulating properties.
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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) | 1989-12-01 | 1990-06-02 | 1990-12-02 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1993-12-01 | 1994-06-02 | 1994-12-02 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1997-12-01 | 1998-06-02 | 1998-12-02 | $7700.00 | Window Closed / Lapsed |