Method of forming a composite structure such as a rocket combustion chamber

Claim 2

A process for forming a high temperature high strength corrosion resistant hollow composite structure comprising: Forming a layer of ductile refractory metal having radially inner and radially outer sides the surface 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 Forming a structural carbon-composite shell in situ against and tightly bonded to said surface on said radially outer side of said layer.

Claim 3

Process of claim 1 including forming said layer of ductile refractory metal and said surface roughness by chemical vapor deposition.

Claim 4

Process of claim 1 wherein said structural carbon-composite shell is a carbon-carbon composite which is formed by applying a carbon filament preform to said surface, infiltrating said preform with a carbon matrix precursor and carbonizing said precursor.

Claim 5

Process of claim 1 wherein said structural carbon-composite shell has a ceramic matrix.

Claim 6

A process for forming a high temperature high strength corrosion resistant hollow composite structure comprising: Forming a removable mandrel having an exterior configuration conforming to the intended interior configuration of said structure; Forming a high temperature corrosion resistant first deposit on the entire exterior surface of said mandrel using chemical vapor deposition; Forming a ductile refractory metal second deposit on the entire exterior surface of said first deposit using chemical vapor deposition under conditions at which said first deposit bonds to said second deposit through an interlayer which comprises an admixture of said first and second deposits; Adjusting the conditions in the last phase of said second chemical vapor deposition to form a roughened dendritic surface on said second deposit having a surface roughness of from approximately 1 to 20 microns; Applying a carbon filament preform to said roughened dendritic surface; Creating a carbon matrix around said carbon filament preform thereby forming a carbon-carbon composite shell tightly bonded to said roughened dendritic surface; and Removing said mandrel.

Claim 7

A process for forming a high temperature high strength corrosion resistant hollow composite structure comprising: Forming a removable mandrel having an exterior configuration conforming to the intended interior configuration of said structure; Forming a high temperature corrosion resistant first deposit on the entire exterior surface of said mandrel using chemical vapor deposition; Forming a ductile refractory metal second deposit on the entire exterior surface of said first deposit using chemical vapor deposition under conditions at which said first deposit bonds to said second deposit through an interlayer which comprises an admixture of said first and second deposits; Adjusting the conditions in the last phase of said second chemical vapor deposition to form a roughened dendritic surface on said second deposit having a surface roughness of from approximately 1 to 20 microns; Applying a carbon filament preform to said roughened dendritic surface; Creating a carbon matrix around said carbon filament preform thereby forming a carbon-carbon composite shell tightly bonded to said roughened dendritic surface; and Removing said mandrel.

Claim 8

Process of claim 5 wherein said second deposit is of rhenium.

Claim 9

Process of claim 5 wherein said first deposit is of platinum group metal.

Claim 10

A process for forming a rocket combustion chamber comprising: Forming a removable mandrel having an exterior configuration conforming to the intended configuration of the interior of the rocket combustion chamber; Depositing at least a layer of ductile refractory metal on the outside surface of said mandrel utilizing chemical vapor deposition; Forming a dendritic roughened surface on the exterior of said layer of ductile refractory metal, said roughened surface comprising free standing grains present in a density of from approximately 500,000 to 15,000,000 grains per square centimeter; Forming a carbon filament preform in situ against said roughened surface; Infiltrating said preform with a carbon precursor, and carbonizing said precursor to form a carbon-carbon composite shell tightly bonded to said dendritic roughened surface; and Removing said mandrel.

Claim 11

A process for forming a rocket combustion chamber comprising: Forming a removable mandrel having an exterior configuration conforming to the intended configuration of the interior of the rocket combustion chamber; Depositing at least a layer of ductile refractory metal on the outside surface of said mandrel utilizing chemical vapor deposition; Forming a dendritic roughened surface on the exterior of said layer of ductile refractory metal, said roughened surface comprising free standing grains present in a density of from approximately 500,000 to 15,000,000 grains per square centimeter; Forming a carbon filament preform in situ against said roughened surface; Infiltrating said preform with a carbon precursor, and carbonizing said precursor to form a carbon-carbon composite shell tightly bonded to said dendritic roughened surface; and Removing said mandrel.