# US 5,701,670 A · Method of making rocket engine combustion chamber utilizing "slide in" port liner

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- Number: US 5,701,670 A
- Document ID: US5701670A
- Status: Granted
- Kind: A
- Application number: 08/264,263
- Filed: 1994-06-23
- Granted: 1997-12-30
- Earliest claimed: 1994-06-23
- Assignees: Boeing North American, Inc.
- Inventors: Steven C. Fisher; Theodore C. Adams; Maynard L. Stangeland; Jacob Rietdyk; Paul R. Winans
- Web page: https://patentgrep.com/patent/US5701670A

## CPC

- B23P 15/008: {Rocket engine parts, e.g. nozzles, combustion chambers}
- F02K 9/972: {Fluid cooling arrangements for nozzles (F02K9/64 takes precedence)}
- Y10T 29/49346: Rocket or jet device making
- Y10T 29/49826: Assembling or joining
- B23P: METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS (arrangements for copying or controlling B23Q)
- F02K: JET-PROPULSION PLANTS (features of jet-propulsion plants common to gas-turbine plants, air intakes or fuel supply control of air-breathing jet-propulsion plants F02C7/00, F02C9/00)
- Y10T: TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION

## Abstract

A method of fabricating a rocket engine combustion chamber comprising assembling a liner having cooling channels, a plurality of throat support sections, and a structural jacket having inlet and outlet manifolds. Then heating the assembly in a pressurized furnace to bond the assembled parts to each other.

## Claims

### Claim 1

A method of making a rocket engine combustion chamber comprising:
forming a coolant liner having an outside surface;
forming a plurality of coolant channels on the outside surface of the coolant liner so that the surface has a plurality of lands;
forming at least two throat support sections;
assembling the throat support sections together around the outside surface of the coolant liner;
forming a structural jacket having an inside cavity, an inlet manifold, inlet feed passages, an outlet manifold, and outlet feed passages;
inserting the coolant liner with surrounding throat support sections into the structural jacket inside cavity to form a combustion chamber assembly;
forming sealing joints between the coolant liner and the structural jacket to seal off the coolant channels;
capping the inlet and outlet manifolds;
inserting the combustion chamber assembly into a pressure furnace;
pressurizing the furnace, thus forcing the coolant liner, throat support sections, and structural jacket into contact;
heating the combustion chamber assembly to a bonding temperature for bonding the assembled parts to each other to form the combustion chamber while pressurizing the pressure furnace.

### Claim 2 (depends on 1)

A method of making a rocket engine combustion chamber as in claim 1 further comprising the steps of:
evacuating the coolant passages and manifolds for lowering the pressure therein thus drawing the coolant liner, throat support sections and structural jacket into contact.

### Claim 3 (depends on 1)

A method of making a rocket engine combustion chamber as in claim 1 further comprising the steps of:
cooling the combustion chamber in the furnace and removing the pressure from the furnace;
taking the combustion chamber out of the pressure furnace;
removing excess seal joint material;
removing the plugs.

### Claim 4 (depends on 1)

A method of making a rocket engine combustion chamber as in claim 1 further comprising the steps of:
plating the coolant liner, throat support sections and structural jacket prior to bonding to form a better bond between the parts.

### Claim 5 (depends on 4)

A method of making a rocket engine combustion chamber as in claim 4 further comprising the steps of:
inserting a braze alloy foil between the coolant liner, throat support sections and structural jacket prior to bonding to form a better bond between the parts.

### Claim 6 (depends on 4)

A method of making a rocket engine combustion chamber as in claim 4 wherein:
nickel is plated to the structural jacket and gold is plated to the coolant liner.

### Claim 7 (depends on 3)

A method of making a rocket engine combustion chamber as in claim 3 wherein:
nickel and gold are used for plating prior to bonding.

### Claim 8

A method of making a rocket engine combustion chamber comprising:
forming a closed out coolant liner having an outside surface;
forming at least two throat support sections;
assembling the throat support sections together around the outside surface of the coolant liner;
forming a structural jacket having an inside cavity, an inlet manifold, inlet feed passages, an outlet manifold, and outlet feed passages;
inserting the coolant liner with surrounding throat support sections into the structural jacket inside cavity to form a combustion chamber assembly;
forming sealing joints between the coolant liner and the structural jacket to seal off the coolant channels;
capping the inlet and outlet manifolds;
inserting the combustion chamber assembly into a pressure furnace;
pressurizing the furnace, thus forcing the coolant liner, throat support sections, and structural jacket into contact;
heating the combustion chamber assembly to a bonding temperature for bonding the assembled parts to each other to form the combustion chamber while pressurizing the pressure furnace.

### Claim 9 (depends on 8)

A method of making a rocket engine combustion chamber as in claim 8 further comprising the steps of:
evacuating the coolant passages and manifolds for lowering the pressure therein thus drawing the coolant liner, throat support sections and structural jacket into contact.