US4738902A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Gas turbine engine and composite parts
Assignee: RTX Corp
•
Filing: 1986-02-19
•
Granted: 1988-04-19
•
Expires: 2006-02-19
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
2026-10-29 17:09
CPC Classifications
F; F01; F01D; F01D5/00; F01D5/12; F01D5/28; F01D5/284; B; B32; B32B; B32B18/00; C; C03; C03C; C03C14/00; C03C14/002; C04; C04B; C04B35/00; C04B35/01; C04B35/16; C04B35/18; C04B35/19; C04B35/622; C04B35/64; C04B35/645; C04B35/71; C04B35/78; C04B35/80; F01D25/00; F01D25/005; F01D5/282; F23; F23R; F23R3/00; F23R3/007; C03C2214/00; C03C2214/02; C03C2214/20; C04B2235/00; C04B2235/02; C04B2235/30; C04B2235/32; C04B2235/3201; C04B2235/3203; C04B2235/50; C04B2235/52; C04B2235/5208; C04B2235/5216; C04B2235/524; C04B2235/5244; C04B2235/5264; C04B2235/5268; C04B2235/70; C04B2235/96; 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; Y10S; Y10S428/00; Y10S428/902; Y10T; Y10T428/00; Y10T428/24; Y10T428/24058; Y10T428/24074; Y10T428/24116; Y10T428/24132; Y10T428/249921; Y10T428/249924; Y10T428/249928; Y10T428/249929; Y10T428/29; Y10T428/2913; Y10T428/2918
Claims Analysis
Total Claims: 39
Claim 1
Independent Claim
95 words
A gas turbine engine core engine component blade, vane, disk, side plate, seal, combustor liner, flap, burner case structure, or turbine case structure, comprising a silicon carbide fiber reinforced glass composite consisting essentially of about 30% to about 70% by volume silicon carbide fibers in a glass matrix selected from the group consisting of borosilicate glass, high silica content glass, aluminosilicate glass and mixtures thereof, the composite having a fracture toughness exemplified by a critical stress intensity factor above about 15,000 psi (inch) 1/2 , high temperature strength, high temperature oxidation stability and insulating properties.
Claim 2
Dependent Claim
95 words
A gas turbine engine core engine component blade, vane, disk, side plate, seal, combustor liner, flap, burner case structure, or turbine case structure, comprising a silicon carbide fiber reinforced glass composite consisting essentially of about 30% to about 70% by volume silicon carbide fibers in a glass matrix selected from the group consisting of borosilicate glass, high silica content glass, aluminosilicate glass and mixtures thereof, the composite having a fracture toughness exemplified by a critical stress intensity factor above about 15,000 psi (inch) 1/2 , high temperature strength, high temperature oxidation stability and 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 multiflament silicon carbide yarn with an average filament diameter of up to 50 microns.
Claim 7
Dependent Claim
19 words
The component of claim 5 wherein the yarn has an averge filiment diameter of 5 microns to 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
21 words
The composite of claim 1 having a flexural strength above about 60,000 psi up to a temperature of about 600° C.
Claim 10
Dependent Claim
16 words
The composite of claim 1 wherein the fibers have a substantially 0°/90° orientation within the composite.
Claim 11
Dependent Claim
19 words
The composite of claim 9 wherein the silicon carbide fiber is present in an amount about 50% by volume.
Claim 12
Dependent Claim
20 words
The component of claim 1 having a flexural strength above about 150,000 psi at temperatures up to about 700° C.
Claim 13
Dependent Claim
16 words
The component of claim 1 having a fracture toughness above about 25,000 psi (inch) 1/2 .
Claim 14
Dependent Claim
97 words
A gas turbine engine core engine component blade, vane, disk, side plate, seal, combustor liner, flap, burner case structure, or turbine case structure, comprising about 15% to about 50% by volume high strength and high modulus of elasticity discontinuous silicon carbide fibers laid up in substantially in-plane random orientation in a glass matrix selected from the group consisting of borosilicate glass, high silica content glass, aluminosilicate glass, and mixtures thereof, so as to produce strength and fracture toughness properties greater than that of the glass matrix at temperatures in excess of 300° C. in an oxidizing environment.
Claim 15
Dependent Claim
97 words
A gas turbine engine core engine component blade, vane, disk, side plate, seal, combustor liner, flap, burner case structure, or turbine case structure, comprising about 15% to about 50% by volume high strength and high modulus of elasticity discontinuous silicon carbide fibers laid up in substantially in-plane random orientation in a glass matrix selected from the group consisting of borosilicate glass, high silica content glass, aluminosilicate glass, and mixtures thereof, so as to produce strength and fracture toughness properties greater than that of the glass matrix at temperatures in excess of 300° C. in an oxidizing environment.
Claim 16
Dependent Claim
26 words
The component of claim 13 having a flexural strength greater than 10,000 psi (68.8 MPa) at temperatures in excess of 300° C. in an oxidizing environment.
Claim 17
Dependent Claim
26 words
The component of claim 13 having a flexural strength greater than 20,000 psi (138 MPa) at temperatures in excess of 300° C. in an oxidizing environment.
Claim 18
Dependent Claim
25 words
The component of claim 13 having a fracture toughness greater than 3 MPa/m 3/2 at temperatures in excess of 300° C. in an oxidizing environment.
Claim 19
Dependent Claim
25 words
The component of claim 13 having a fracture toughness greater than 5 MPa/m 3/2 at temperatures in excess of 300° C. in an oxidizing environment.
Claim 20
Dependent Claim
103 words
A gas turbine engine core engine component blade, vane, disk, side plate, seal, combustor liner, flap, burner case structure, or turbine case structure, comprising about 15% to about 50% by volume high strength, high modulus of elasticity silicon carbide fibers having an average length of about 1 cm to about 3 cm laid up in substantially in-plane random orientation in a low coefficient of thermal expansion glass matrix selected from the group consisting of borosilicate glass, high silica content glass, aluminosilicate glass and mixtures thereof, producing a composite with flexural strength and fracture toughness properties greater than the glass matrix at elevated temperatures.
Claim 21
Dependent Claim
103 words
A gas turbine engine core engine component blade, vane, disk, side plate, seal, combustor liner, flap, burner case structure, or turbine case structure, comprising about 15% to about 50% by volume high strength, high modulus of elasticity silicon carbide fibers having an average length of about 1 cm to about 3 cm laid up in substantially in-plane random orientation in a low coefficient of thermal expansion glass matrix selected from the group consisting of borosilicate glass, high silica content glass, aluminosilicate glass and mixtures thereof, producing a composite with flexural strength and fracture toughness properties greater than the glass matrix at elevated temperatures.
Claim 22
Dependent Claim
99 words
A gas turbine engine core engine component blade, vane, disk, side plate, seal, combustor liner, flap, burner case structure, or turbine case structure, consisting essentially of about 15% to about 50% by volume high strength and high modulus of elasticity discontinuous silicon carbide fibers laid up in substantially in-plane random orientation in a substantially titanium-free glass-ceramic matrix selected from the group consisting of lithium aluminosilicate, magnesium aluminosilicate, barium aluminosilicate, aluminosilicate, and combinations thereof, so as to produce strength and fracture toughness properties greater than that of the matrix at temperatures in excess of 800° C. in an oxidizing environment.
Claim 23
Dependent Claim
99 words
A gas turbine engine core engine component blade, vane, disk, side plate, seal, combustor liner, flap, burner case structure, or turbine case structure, consisting essentially of about 15% to about 50% by volume high strength and high modulus of elasticity discontinuous silicon carbide fibers laid up in substantially in-plane random orientation in a substantially titanium-free glass-ceramic matrix selected from the group consisting of lithium aluminosilicate, magnesium aluminosilicate, barium aluminosilicate, aluminosilicate, and combinations thereof, so as to produce strength and fracture toughness properties greater than that of the matrix at temperatures in excess of 800° C. in an oxidizing environment.
Claim 24
Dependent Claim
26 words
The component of claim 19 having a flexural strength greater than 10,000 psi (68.8 MPa) at temperatures in excess of 800° C. in an oxidizing environment.
Claim 25
Dependent Claim
26 words
The component of claim 19 having a flexural strength greater than 20,000 psi (138 MPa) at temperatures in excess of 800° C. in an oxidizing environment.
Claim 26
Dependent Claim
25 words
The component of claim 19 having a fracture toughness greater than 3 MPa/m 3/2 at temperatures in excess of 800° C. in an oxidizing environment.
Claim 27
Dependent Claim
24 words
The component of claim 19 having a fracture toughness greater than 5 MPa/m3/2 at temperatures in excess of 800° C. in an oxidizing environment.
Claim 28
Dependent Claim
96 words
A gas turbine engine core engine component blade, vane, disk, side plate, seal, combustor liner, flap, burner case structure, or turbine case structure, consisting essentially of about 15% to about 50% by volume high strength, high modulus of elasticity silicon carbide fibers having an average length of about 1 cm to about 3 cm laid up in substantially in-plane random orientation in a substantially titanium-free glass-ceramic matrix of lithium aluminosilicate, magnesium aluminosilicate, barium aluminosilicate, aluminosilicate, and combinations thereof, producing a composite with flexural strength and fracture toughness properties greater than the ceramic matrix at elevated temperatures.
Claim 29
Dependent Claim
96 words
A gas turbine engine core engine component blade, vane, disk, side plate, seal, combustor liner, flap, burner case structure, or turbine case structure, consisting essentially of about 15% to about 50% by volume high strength, high modulus of elasticity silicon carbide fibers having an average length of about 1 cm to about 3 cm laid up in substantially in-plane random orientation in a substantially titanium-free glass-ceramic matrix of lithium aluminosilicate, magnesium aluminosilicate, barium aluminosilicate, aluminosilicate, and combinations thereof, producing a composite with flexural strength and fracture toughness properties greater than the ceramic matrix at elevated temperatures.
Claim 30
Dependent Claim
99 words
A gas turbine engine containing at least one core engine component blade, vane, disk, side plate, seal, combustor liner, flap, burner case structure, or turbine case structure, comprising a silicon carbide fiber reinforced glass composite consisting essentially of about 30% to about 70% by volume silicon carbide fibers in a glass matrix selected from the group consisting of borosilicate glass, high silica content glass, aluminosilicate glass and mixtures thereof, the composite having a fracture toughness exemplified by a critical stress intensity factor above about 15,000 psi (inch) 1/2 , high temperature strength, high temperature oxidation stability and insulating properties.
Claim 31
Dependent Claim
99 words
A gas turbine engine containing at least one core engine component blade, vane, disk, side plate, seal, combustor liner, flap, burner case structure, or turbine case structure, comprising a silicon carbide fiber reinforced glass composite consisting essentially of about 30% to about 70% by volume silicon carbide fibers in a glass matrix selected from the group consisting of borosilicate glass, high silica content glass, aluminosilicate glass and mixtures thereof, the composite having a fracture toughness exemplified by a critical stress intensity factor above about 15,000 psi (inch) 1/2 , high temperature strength, high temperature oxidation stability and insulating properties.
Claim 32
Dependent Claim
101 words
A gas turbine engine containing at least one core engine component blade, vane, disk, side plate, seal, combustor liner, flap, burner case structure, or turbine case structure, comprising about 15% to about 50% by volume high strength and high modulus of elasticity discontinuous silicon carbide fibers laid up in substantially in-plane random orientation in a glass matrix selected from the group consisting of borosilicate glass, high silica content glass, aluminosilicate glass, and mixtures thereof, so as to produce strength and fracture toughness properties greater than that of the glass matrix at temperatures in excess of 300° C. in an oxidizing environment.
Claim 33
Dependent Claim
101 words
A gas turbine engine containing at least one core engine component blade, vane, disk, side plate, seal, combustor liner, flap, burner case structure, or turbine case structure, comprising about 15% to about 50% by volume high strength and high modulus of elasticity discontinuous silicon carbide fibers laid up in substantially in-plane random orientation in a glass matrix selected from the group consisting of borosilicate glass, high silica content glass, aluminosilicate glass, and mixtures thereof, so as to produce strength and fracture toughness properties greater than that of the glass matrix at temperatures in excess of 300° C. in an oxidizing environment.
Claim 34
Dependent Claim
107 words
A gas turbine engine containing at least one core engine component blade, vane, disk, side plate, seal, combustor liner, flap, burner case structure, or turbine case structure, comprising about 15% to about 50% by volume high strength, high modulus of elasticity silicon carbide fibers having an average length of about 1 cm to about 3 cm laid up in substantially in-plane random orientation in a low coefficient of thermal expansion glass matrix selected from the group consisting of borosilicate glass, high silica content glass, aluminosilicate glass and mixtures thereof, producing a composite with flexural strength and fracture toughness properties greater than the glass matrix at elevated temperatures.
Claim 35
Dependent Claim
107 words
A gas turbine engine containing at least one core engine component blade, vane, disk, side plate, seal, combustor liner, flap, burner case structure, or turbine case structure, comprising about 15% to about 50% by volume high strength, high modulus of elasticity silicon carbide fibers having an average length of about 1 cm to about 3 cm laid up in substantially in-plane random orientation in a low coefficient of thermal expansion glass matrix selected from the group consisting of borosilicate glass, high silica content glass, aluminosilicate glass and mixtures thereof, producing a composite with flexural strength and fracture toughness properties greater than the glass matrix at elevated temperatures.
Claim 36
Dependent Claim
103 words
A gas turbine engine containing at least one core engine component blade, vane, disk, side plate, seal, combustor liner, flap, burner case structure, or turbine case structure, consisting essentially of about 15% to about 50% by vo-ume high strength and high modulus of elasticity discontinuous silicon carbide fibers laid up in substantially in-plane random orientation in a substantially titanium-free glass-ceramic matrix selected from the group consisting of lithium aluminosilicate, magnesium aluminosilicate, barium aluminosilicate, aluminosilicate, and combinations thereof, so as to produce strength and fracture toughness properties greater than that of the matrix at temperatures in excess of 800° C. in an oxidizing environment.
Claim 37
Dependent Claim
103 words
A gas turbine engine containing at least one core engine component blade, vane, disk, side plate, seal, combustor liner, flap, burner case structure, or turbine case structure, consisting essentially of about 15% to about 50% by vo-ume high strength and high modulus of elasticity discontinuous silicon carbide fibers laid up in substantially in-plane random orientation in a substantially titanium-free glass-ceramic matrix selected from the group consisting of lithium aluminosilicate, magnesium aluminosilicate, barium aluminosilicate, aluminosilicate, and combinations thereof, so as to produce strength and fracture toughness properties greater than that of the matrix at temperatures in excess of 800° C. in an oxidizing environment.
Claim 38
Dependent Claim
100 words
A gas turbine engine containing at least one core engine component blade, vane, disk, side plate, seal, combustor liner, flap, burner case structure, or turbine case structure, consisting essentially of about 15% to about 50% by volume high strength, high modulus of elasticity silicon carbide fibers having an average length of about 1 cm to about 3 cm laid up in substantially in-plane random orientation in a substantially titanium-free glass-ceramic matrix of lithium aluminosilicate, magnesium aluminosilicate, barium aluminosilicate, aluminosilicate, and combinations thereof, producing a composite with flexural strength and fracture toughness properties greater than the ceramic matrix at elevated temperatures.
Claim 39
Dependent Claim
100 words
A gas turbine engine containing at least one core engine component blade, vane, disk, side plate, seal, combustor liner, flap, burner case structure, or turbine case structure, consisting essentially of about 15% to about 50% by volume high strength, high modulus of elasticity silicon carbide fibers having an average length of about 1 cm to about 3 cm laid up in substantially in-plane random orientation in a substantially titanium-free glass-ceramic matrix of lithium aluminosilicate, magnesium aluminosilicate, barium aluminosilicate, aluminosilicate, and combinations thereof, producing a composite with flexural strength and fracture toughness properties greater than the ceramic matrix at elevated temperatures.
References Cited (Backward Citations)
US4324843A
Cited
US4341826A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1991-04-19 | 1991-10-19 | 1992-04-19 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1995-04-19 | 1995-10-19 | 1996-04-19 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1999-04-19 | 1999-10-19 | 2000-04-19 | $7700.00 | Window Closed / Lapsed |