Aircraft transparency having chemically tempered lithia-alumina-silica containing glass and method of making the chemically tempered glass
An aircraft transparency in a glass piece, wherein the glass piece includes a chemically tempered first major surface and a chemically tempered opposite second major surface, a first case depth begins at the first major surface, a second case depth begins at the second major surface, and a tensile stress zone is within the glass piece between the end points of the first and the second case depths. The glass between the end points of the first and second case depth has a glass composition including: Ingredient Percent by weight SiO 2 60 to 75; Al 2 O 3 18 to 28; and Li 2 O 3 to 9, and the glass has at least one of the following properties (a) a log 10 viscosity temperature of at least 1413° F. and (b) a liquidus temperature of at least 2436° F.
1. An aircraft transparency comprising a glass piece, the glass piece comprising:
a chemically tempered first major surface and an opposite second major surface;
a case depth, wherein the case depth is defined as a distance from the first major surface of the glass piece toward the second major surface, the distance ending at a position within the glass piece at which the glass piece has zero stress, and
a tensile stress zone within the glass piece at a depth from the first major surface greater than the distance of the case depth from the first major surface, wherein glass in the tensile stress zone has a glass composition comprising:
Ingredient
Percent by weight
SiO 2
60 to 75;
Al 2 O 3
18 to 29
Li 2 O
3 to 9; and
ZrO 2
0 to 3;
wherein percent by weight (“wt %”) of Al 2 O 3 +ZrO 2 is in the range 18 to 29 wt %, and wherein the glass in the tensile stress zone has at least one of the following properties: (a) a log 10 viscosity temperature of at least 1280° F. (694° C.) and (b) a liquidus temperature of at least 2350° F. (1288° C.), and has an unabraded modulus of rupture in the range of 71 to 112 thousand pounds per square inch (“ KPSI”).
2. The aircraft transparency according to claim 1 , wherein the glass in the tensile stress zone has a log 10 viscosity in the temperature range of 1328° F. (720° C.) to 1499° F. (815° C.); a liquidus temperature in the temperature range of 2437° F. (1336° C.) to 2575° F. (1413° C.), and a log 7.6 softening point temperature in the temperature range of 1544° F. (840° C.) to 1724° F. (940° C.).
3. The aircraft transparency according to claim 2 , wherein the unabraded modulus of rupture is in the range of 76 to 106 KPSI and wherein the glass piece has at least one of the following properties:
a case depth in the range of 7 to 13.3 mils, an abraded modulus of rupture in the range of 72 to 78.6 thousand pounds per square inch (“KPSI”), a center tension in the range of 6.1 to 10.3 KPSI, a center tension area in the range of 554 to 1033 pounds/inch, a Vickers hardness 1000 in the range of 600 to 614 kilograms per square millimeter (“kg/mm 2 ”), and a Knoop hardness 1000 in the range of 503 to 526 kg/mm 2 .
4. The aircraft transparency according to claim 2 , wherein the glass piece has at least one of the following properties: a case depth in the range of 11.5 to 17.4 mils, an abraded modulus of rupture in the range of 77 to 78 thousand pounds per square inch (“KPSI”), center tension in the range of 6.1 to 10.3 KPSI, a center tension area in the range of 749 to 1080 pounds/inch, a Vickers hardness 1000 in the range of 598 to 606 kilograms per square millimeter (“kg/mm 2 ”), and a Knoop hardness 1000 in the range of 505 to 522 kg/mm 2 .
5. . The aircraft transparency according to claim 1 , wherein the case depth is a first case depth and further comprising a second case depth, wherein the tensile stress zone is between the first and the second case depths, and the second case depth is defined as a distance from the second major surface of the glass piece toward the first major surface and ending at a position within the glass piece at which there is zero stress.
6. The aircraft transparency according to claim 5 , wherein the glass piece submerged into a container of boiling 0.50 wt % sulfuric acid for 30 minutes has weight loss in the range of 0.002 to 0.014 milligrams per square centimeter-hour.
7. The aircraft transparency according to claim 1 further comprising a mounting frame wherein the glass piece is secured in the mounting frame.
8. The aircraft transparency according to claim 7 , wherein the case depth is a first case depth and further comprising a second case depth, wherein the tensile stress zone is between the first and the second case depths, and the second case depth is defined as a distance from the second major surface of the glass piece toward the first major surface and ending at a position within the glass piece at which there is zero stress.
9. An aircraft transparency comprising a glass piece, the glass piece comprising:
a chemically tempered first major surface and a chemically tempered opposite second major surface;
a first case depth and a second case depth, wherein the first case depth is defined as a first distance from the first major surface of the glass piece toward the second major surface, the first distance ending a first position within the glass piece at which there is zero stress and the second case depth is defined as a second distance from the second major surface of the glass piece toward the first major surface, the second distance ending a second position within the glass piece at which there is zero stress, wherein the first position is spaced from the second position, and
a tensile stress zone defined as interior glass, wherein the interior glass is within the glass piece between the first and the second positions, wherein the interior glass has a glass composition comprising:
Ingredient
Percent by weight
SiO 2
60 to 75;
Na 2 O
0.39 to 2.00
Al 2 O 3
18 to 28; and
Li 2 O
3 to 9;
wherein the unabraded modulus of rupture is in the range of 71 to 112 thousand pounds per square inch (“KPSI”) and wherein the glass composition has (a) a log 10 viscosity temperature of at least 1413° F. and (b) a liquidus temperature of at least 2436° F.
10. The aircraft transparency according to claim 9 , wherein the glass within the first case depth has a lower concentration of lithium than the interior glass.
11. The aircraft transparency according to claim 9 , wherein the first distance is in the range of 7 to 16.5 mils.
12. The aircraft transparency according to claim 9 , wherein the glass composition of the interior glass comprises:
Ingredient
Percent by weight
SiO 2
64.83 to 69.29;
Al 2 O 3
21.97 to 23.51;
Li 2 O
4.94 to 6.50;
K 2 O
0.07 to 0.10;
where the combined percent by weight (“wt %”) of Na 2 O and K 2 O is in the range of 0.49 to 2.07 wt %.
13. The aircraft transparency according to claim 12 , wherein the glass piece has a center tension in the range of 5,700 to 14,900 pound per square inch.
14. The aircraft transparency according to claim 12 , wherein the glass piece has a center tension area in the range of 632 to 979 pounds per inch.
15. The aircraft transparency according to claim 12 , wherein the glass piece has an unabraded modulus of rupture in the range of 76,000 to 106,000 pounds per square inch.
16. The aircraft transparency according to claim 12 , wherein the glass piece has a Vickers's hardness 1000 in the range of 586 to 614 kilograms per square millimeters measured on one of the major surfaces.
17. The aircraft transparency according to claim 9 further comprising a mounting frame wherein the glass piece is a layer of a laminate and the laminate is secured in the mounting frame.
18. The aircraft transparency according to claim 1 further comprising Na 2 O in the range of 0.39 to 2.00 wt %.
19. The aircraft transparency according to claim 1 further comprising Na 2 O in the range of 0.05 to 1.5 wt %.
20. The aircraft transparency according to claim 9 , wherein Na 2 O is in the range of 0.05 to 1.5 wt %.