Titanium alloy (15V-3Cr-3Sn-3Al) for aircraft data recorder
AssigneeSundstrand Data Control, Inc.
InventorsKenneth W. White, William F. Spurr
Life of this patent
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Abstract
An aircraft flight data recorder housing comprising a titanium alloy having a nominal composition of 15 weight percent vanadium, 3 weight percent chromium, 3 weight percent tin, and 3 weight percent aluminum with the balance being titanium and, within limitations, certain trace elements. The alloy is simultaneously hot formed and solution heat treated at temperatures on the order of 1400.degree. F. to 1500.degree. F. to fabricate the recorder housing.
Claims14
A flight data recorder housing comprising a titanium alloy consisting essentially of
- ______________________________________ Element Weight percent (wt. %) ______________________________________ V 14 to 16 Cr 2.5 to 3.5 Sn 2.5 to 3.5 Al 2.5 to 3.5 O.sub.2 0.13 max N.sub.2 0.03 max C 0.03 max H.sub.2 0.015 max Fe 0.30 max Y 0.005 max Residual elements, each 0.10 max Residual elements, total 0.30 max Ti Balance, ______________________________________
- said housing having been simultaneously formed and solution heat treated at an elevated temperature, said alloy having been aged to an ultimate tensile strength less than 200 ksi.
A method for preparing a flight data recorder housing comprising a titanium alloy exhibiting high strength and fracture toughness wherein said alloy consists essentially of
- ______________________________________ Element Weight percent (wt. %) ______________________________________ V 14 to 16 Cr 2.5 to 3.5 Sn 2.5 to 3.5 Al 2.5 to 3.5 O.sub.2 0.13 max N.sub.2 0.03 max C 0.03 max H.sub.2 0.015 max Fe 0.30 max Y 0.005 max Residual elements, each 0.10 max Residual elements, total 0.30 max Ti Balance, ______________________________________
- said method comprising the steps of:
- a. formulating said alloy and creating an ingot,
- b. forging said ingot and rolling sheet stock therefrom,
- c. simultaneously solution treating and forming a flight data recorder housing from said sheet stock at an elevated temperature, and
- d. aging said alloy to an ultimate tensile strength level less than 200 ksi.
Dependencies are inferred from the claim text.