Composite structure

• US 5,780,157 A
• Filed: 06/06/1994
• Issued: 07/14/1998
• Est. Priority Date: 06/06/1994
• Status: Expired due to Term

• Current Assignee: Ultramet Co.
• Original Assignee: Ultramet Co.
• Inventors: Williams, Brian E., Kaplan, Richard B., Tuffias, Robert H.
• Primary Examiner(s): SPEER, TIMOTHY M
• Application Number:
  US08/254,515
• Time in Patent Office: 1,499 Days
• Field of Search: 428/408, 428/688, 428/689, 428/699, 428/469, 428/472, 428/457, 428/141, 428/142, 244/133
• US Class Current: 428/408
• CPC Class Codes: C23C 16/01 on temporary substrates, e.g. substrates subsequently removed by etching
• CPC Class Codes: C23C 16/06 characterised by the deposition of metallic material
• CPC Class Codes: C23C 16/56 After-treatment
• CPC Class Codes: F02K 9/346 Liners, e.g. inhibitors
• CPC Class Codes: F02K 9/62 Combustion or thrust chambers
• CPC Class Codes: Y10T 29/49346 Rocket or jet device making
• CPC Class Codes: Y10T 428/30 Self-sustaining carbon mass or layer with impregnant or other layer
• CPC Class Codes: Y10T 428/31678 Of metal

Abstract

A refractory composite structure comprising a ductile refractory metallic layer with a roughened surface which is tightly bonded to a refractory composite structural shell. The roughened surface is dendritic in form and is produced by chemical vapor deposition techniques.

Claims

1. A high temperature corrosion resistant composite structure comprising:

a refractory metallic layer having two sides, one of said sides having a roughened surface, said roughened surface comprising from approximately 500,000 to 15,000,000 free standing metallic grains per square centimeter; and

a refractory structural composite shell comprising a matrix and filamentaceous inclusions tightly bonded to said roughened surface.

2. A rocket combustion chamber comprising:

a refractory metallic layer having two sides, one of said sides having a roughened surface with a surface roughness of from approximately 1 to 20 microns, the roughness of said roughened surface comprising free standing particles having an average diameter of from approximately 1 to 20 microns; and

a refractory structural composite shell comprising a matrix and filamentaceous inclusions tightly bonded to said roughened surface, said refractory metallic layer being adapted to protect said refractory structural composite shell from combustion products.

3. A rocket combustion chamber of claim 2 wherein said matrix comprises a ceramic material.

4. A rocket combustion chamber of claim 2 wherein said chamber has a generally circular cross section and exhibits a hoop strength, and from approximately 50 to 90 percent of said hoop strength being provided by said refractory structural composite shell.

5. A high temperature corrosion resistant composite structure comprising:

a layer of ductile refractory metal having two sides and a tensile strength of greater than approximately 5,000 pounds per square inch at a temperature of approximately 1,500 degrees centigrade, a face of said layer on one of said sides having a roughness of from approximately 1 to 20 microns; and

a structural carbon-composite shell comprising a matrix and filamentaceous inclusions tightly bonded to said face of said layer, said layer of ductile refractory metal being adapted to protect said structural carbon-composite shell.

6. A high temperature corrosion resistant composite structure comprising:

a layer of ductile refractory metal having radially inner and radially outer sides and a tensile strength of greater than approximately 5,000 pounds per square inch at a temperature of approximately 1,500 degrees centigrade, a face of said layer on said radially outer side having a roughness of from approximately 1 to 20 microns, said roughness being substantially formed by a dendritic growth of said refractory metal; and

a structural carbon-composite shell tightly bonded to said face on said radially outer side of said layer.

7. A high temperature corrosion resistant composite structure comprising:

a generally circular refractory metallic layer having radially inner and radially outer sides, said radially outer side having a roughened surface having a roughness of from approximately 1 to 20 microns; and

a refractory structural composite shell comprising a matrix and filamentaceous inclusions tightly bonded to said roughened surface, said refractory metallic layer being adapted to protect said refractory structural composite shell.

8. A high temperature corrosion resistant composite structure of claim 7 wherein said matrix comprises a ceramic.

9. A high temperature corrosion resistant composite structure of claim 7 wherein said matrix comprises carbon.