High performance, thin metal lined, composite overwrapped pressure vessel

• US 5,822,838 A
• Filed: 07/22/1996
• Issued: 10/20/1998
• Est. Priority Date: 02/01/1996
• Status: Expired

• Current Assignee: Lockheed Martin Corporation (Martin Marietta Corporation)
• Original Assignee: Lockheed Martin Corporation (Martin Marietta Corporation)
• Inventors: Seal, Ellis C., Elfer, Norman C.
• Primary Examiner(s): Pollard, Steven M.
• Application Number:
  US08/681,147
• Time in Patent Office: 820 Days
• Field of Search: 220/576, 220/590, 220/591, 220/589, 29/469.5, 156/172, 219/121.14
• US Class Current: 29/469.5
• CPC Class Codes: B21D 51/24 high-pressure containers, e.g. boilers, bottles
• CPC Class Codes: B23K 15/0046 Welding
• CPC Class Codes: B29C 53/58 helically
• CPC Class Codes: B29C 70/088 and with one or more layers of non-plastics material or non-specified material, e.g. supports
• CPC Class Codes: B29K 2105/0097 Glues or adhesives, e.g. hot melts or thermofusible adhesives
• CPC Class Codes: B29K 2705/00 Use of metals, their alloys or their compounds, for preformed parts, e.g. for inserts
• CPC Class Codes: B29L 2031/7156 Pressure vessels
• CPC Class Codes: F17C 1/06 built-up from wound-on bands or filamentary material, e.g. wires
• CPC Class Codes: F17C 2201/0109 with exteriorly curved end-piece
• CPC Class Codes: F17C 2201/056 Small (<1 m3)
• CPC Class Codes: F17C 2201/058 portable (<30 l)
• CPC Class Codes: F17C 2203/0604 Liners
• CPC Class Codes: F17C 2203/0607 Coatings
• CPC Class Codes: F17C 2203/0621 with three layers
• CPC Class Codes: F17C 2203/0636 Metals
• CPC Class Codes: F17C 2203/0643 Stainless steels
• CPC Class Codes: F17C 2203/0648 Alloys or compositions of metals
• CPC Class Codes: F17C 2203/0665 radially wound
• CPC Class Codes: F17C 2203/0668 axially wound
• CPC Class Codes: F17C 2203/0673 Polymers
• CPC Class Codes: F17C 2205/0305 : Bosses, e.g. boss collars
• CPC Class Codes: F17C 2205/0397 : on both sides of the pressure vessel
• CPC Class Codes: F17C 2209/2154 : Winding
• CPC Class Codes: F17C 2209/2163 : with a mandrel
• CPC Class Codes: F17C 2209/221 : Welding
• CPC Class Codes: F17C 2209/227 : by adhesive means
• CPC Class Codes: F17C 2209/232 : of walls
• CPC Class Codes: F17C 2209/234 : of closing end pieces, e.g. caps
• CPC Class Codes: F17C 2221/011 : Oxygen
• CPC Class Codes: F17C 2221/08 : Ergols, e.g. hydrazine
• CPC Class Codes: F17C 2223/0123 : gaseous, e.g. CNG, GNC
• CPC Class Codes: F17C 2223/036 : Very high pressure (>80 bar)
• CPC Class Codes: F17C 2260/011 : Improving strength
• CPC Class Codes: F17C 2260/012 : Reducing weight
• CPC Class Codes: F17C 2260/013 : Reducing manufacturing time or effort
• CPC Class Codes: F17C 2260/036 : Avoiding leaks
• CPC Class Codes: F17C 2260/042 : Reducing risk of explosion
• CPC Class Codes: F17C 2260/05 : Improving chemical properties
• CPC Class Codes: F17C 2270/0194 : for use under microgravity conditions, e.g. space
• CPC Class Codes: F17C 2270/0197 : Rockets
• CPC Class Codes: Y10T 29/49906 : Metal deforming with nonmetallic bonding

Abstract

An innovative technology for composite overwrapped pressure vessels (COPVs) has been developed which significantly increases cost effectiveness, increases reliability, and reduces weight over state-of-the-art COPVs. This technology combines an innovative thin liner made of a metal having a high modulus of elasticity and a high ductility, a high-performance composite overwrap and a high-performance film adhesive at the overwrap/liner interface. The metal liner can be fabricated from readily available titanium alloy sheet and plate using a combination of spin forming and machining to fabricate components and electron-beam welding for tank assembly. The composite overwrap is filament-wound onto an adhesive-covered titanium liner and the overwrap and adhesive are co-cured in an oven to yield an integrated tank structure.

Claims

1. A method of manufacturing a composite overwrapped pressure vessel, comprising the following steps:

(a) using spin forming, making a liner having first and second dome portions and a cylindrical portion made of a metal having a tensile yield strengthened p.s.i./tensile modulus of elasticity in p.s.i.(F^TY /E) of at least 0.6% and a ductility of at least 5%;

(b) forming first and second bosses made of the metal, the first boss being connected to the first dome portion and the second boss being connected to the second dome portion; and

(c) applying a composite overwrap over the liner, applying filaments of the overwrap onto the liner.

2. The method of claim 1, wherein the dome portions are heat treated to improve performance.

3. The method of claim 1, wherein the dome portions are Ti--6Al--4V and are heat treated by heating them to a temperature of between about 1300°

F. and about 1700°

F. for about 30-120 minutes, then cooling the dome portions to ambient temperature at a rate of not more than about 200°

F. per minute.

4. The method of claim 1, wherein the dome portions are made of a titanium alloy and are spun at a temperature of between about 800°

F. and about 1600°

F.

5. The method of claim 1, wherein the metal is a titanium alloy from the group consisting of:

Ti--6Al--2Sn--4Zr--2Mo, Ti--5Al--2.5Sn, Ti--5Al--2.5Sn ELI, Ti--6Al--2Cb--1Ta--0.8Mo, Ti--8Al--1Mo--1V, Ti--11Sn--5Zr--2Al--1Mo, Ti--6Al--4V, Ti--6Al--4V ELI, Ti--6V--2Sn, Ti--3Al--2.5V, Ti--6Al--2Sn--4Zr--6Mo, Ti--6Al--2Sn--2Zr--2Mo--2Cr--0.25Si, Ti--5Al--2Sn--2Zr--4Mo--4Cr, Ti--13V--11Cr--3Al, Ti--3Al--8V--6Cr--4Mo--4Zr, Ti--15V--3Al--3Cr--3Sn, and Ti--10V--2Fe--3Al.

6. The method of claim 1, wherein the liner is formed in at least two sections and is welded together.

7. The method of claim 6, wherein the welding steps are done with an electron beam weld process.

8. The method of claim 1, wherein the metal has a F^TY /E of at least 0.7%.

9. The method of claim 1, wherein the metal has a ductility of at least 10%.

10. The method of claim 1, further comprising the step of:

applying an adhesive to the liner before applying the overwrap.

11. The method of claim 10, wherein the adhesive is a film adhesive.

12. The method of claim 1, further comprising the step of:

applying a protective coating over the overwrap.

13. The method of claim 1, wherein the composite overwrapped pressure vessel has a PV/W of at least 1.05 million inches.

14. The method of claim 1, wherein the composite overwrapped pressure vessel has a PV/W of at least 1.25 million inches.

15. The method of claim 1, wherein the composite overwrapped pressure vessel has a PV/W of at least 1.45 million inches.

16. The method of claim 1, wherein the liner of the composite overwrapped pressure vessel has a ratio of thickness in inches over diameter in inches of about 1.7×

10^-3.

17. The method of claim 1, wherein the liner of the composite overwrapped pressure vessel has a thickness of not more than 0.025".

18. The method of claim 1, wherein the overwrap comprises a graphite/epoxy composite.

19. The method of claim 1, wherein the ratio of the length of the cylinder to the diameter of the cylinder is at least 1.00.