Rocket engine nozzle and method of fabricating a rocket engine nozzle using pressure brazing
View Patent ↗A method of fabrication of a rocket engine nozzle assembly using pressure brazing generally includes initially assembling a rocket engine nozzle liner into a rocket engine nozzle jacket for a rocket engine nozzle assembly. The rocket engine nozzle assembly may then be sealed. Prior to pressure brazing the rocket engine nozzle assembly, pressure brazing parameters may be determined. The pressure brazing may be performed with the determined pressure brazing parameters to complete the fabrication of the rocket engine nozzle. The rocket engine nozzle assembly may include a rocket engine nozzle jacket and a rocket engine nozzle liner having a plurality of channels, with the space between each channel defining a land, and the rocket engine nozzle liner having at least a pair of endlands disposed at each end thereof. The rocket engine nozzle liner is bonded to the rocket engine nozzle jacket by the endlands being bonded to the nozzle jacket and the lands being pressure brazed to the nozzle jacket.
1. A rocket engine nozzle comprising:
a rocket engine nozzle jacket; and
a rocket engine nozzle liner comprises a multiple of liner pieces, the rocket engine nozzle liner having a plurality of channels, the space between each channel defining a land, and the rocket engine nozzle liner having at least a pair of endlands disposed at each end thereof;
wherein the rocket engine nozzle liner is bonded to the rocket engine nozzle jacket by the endlands being bonded to the nozzle jacket and the lands being pressure brazed to the nozzle jacket using a single pressure brazing operation, the endlands bonded to the nozzle jacket prior to the lands being pressure brazed to the nozzle jacket using the single pressure brazing operation.
2. The rocket engine nozzle of claim 1 , wherein the endlands are welded to the nozzle jacket.
3. The rocket engine nozzle of claim 1 , wherein the endlands are brazed to the nozzle jacket.
4. The rocket engine nozzle of claim 1 , wherein the liner pieces are constructed from different materials.
5. A rocket engine nozzle comprising:
a rocket engine nozzle jacket; and
a rocket engine nozzle liner having a plurality of channels, the space between each channel defines a land, the rocket engine nozzle liner defines a forward endland and an aft endland, the rocket engine nozzle liner bonded to the rocket engine nozzle jacket by the forward endland and the aft endland bonded to the rocket engine nozzle jacket such that any space between the rocket engine nozzle jacket and the rocket engine nozzle liner is sealably enclosed, the lands being pressure brazed to the rocket engine nozzle jacket with a single pressure brazing operation, the bonds at the forward endland and the aft endland define closeout bonds.
6. A rocket engine nozzle comprising:
a rocket engine nozzle jacket; and
a rocket engine nozzle liner having a plurality of channels, the space between each channel defines a land, the rocket engine nozzle liner defines a forward endland and an aft endland, the rocket engine nozzle liner bonded to the rocket engine nozzle jacket by the forward endland and the aft endland bonded to the rocket engine nozzle jacket such that any space between the rocket engine nozzle jacket and the rocket engine nozzle liner is sealably enclosed, the lands being pressure brazed to the rocket engine nozzle jacket with a single pressure brazing operation, the rocket engine nozzle liner includes copper alloy forward section and a steel aft section.
7. A rocket engine nozzle comprising:
a rocket engine nozzle jacket; and
a rocket engine nozzle liner having a plurality of channels, the space between each channel defines a land, the rocket engine nozzle liner defines a forward endland and an aft endland, the rocket engine nozzle liner bonded to the rocket engine nozzle jacket by the forward endland and the aft endland bonded to the rocket engine nozzle jacket such that any space between the rocket engine nozzle jacket and the rocket engine nozzle liner is sealably enclosed, the lands being pressure brazed to the rocket engine nozzle jacket with a single pressure brazing operation, the forward endland and the aft endland each define at least one groove to reduce a bond area between the rocket engine nozzle jacket and the respective forward endland and the aft endland.
8. A rocket engine nozzle comprising:
a rocket engine nozzle jacket; and
a rocket engine nozzle liner having a plurality of channels, the space between each channel defines a land, the rocket engine nozzle liner defines a forward endland and an aft endland, the rocket engine nozzle liner bonded to the rocket engine nozzle jacket by the forward endland and the aft endland bonded to the rocket engine nozzle jacket such that any space between the rocket engine nozzle jacket and the rocket engine nozzle liner is sealably enclosed, the lands being pressure brazed to the rocket engine nozzle jacket with a single pressure brazing operation, the forward endland and the aft endland are bonded to the rocket engine nozzle jacket such that any space between the rocket engine nozzle jacket and the rocket engine nozzle liner is sealably enclosed prior to the lands being pressure brazed to the rocket engine nozzle jacket with the single pressure brazing operation.
9. A rocket engine nozzle comprising:
a rocket engine nozzle jacket; and
a rocket engine nozzle liner comprises a multiple of liner pieces, the rocket engine nozzle liner having a plurality of channels, the space between each channel defining a land, and the rocket engine nozzle liner having at least a pair of endlands disposed at each end thereof
wherein the rocket engine nozzle liner is bonded to the rocket engine nozzle jacket by the endlands being bonded to the nozzle jacket and the lands being pressure brazed to the nozzle jacket using a single pressure brazing operation, the endlands contained within the nozzle jacket.
10. A rocket engine nozzle comprising:
a rocket engine nozzle jacket; and
a rocket engine nozzle liner comprises a multiple of liner pieces, the rocket engine nozzle liner having a plurality of channels, the space between each channel defining a land, and the rocket engine nozzle liner having at least a pair of endlands disposed at each end thereof;
wherein the rocket engine nozzle liner is bonded to the rocket engine nozzle jacket by the endlands being bonded to the nozzle jacket and the lands being pressure brazed to the nozzle jacket using a single pressure brazing operation, the forward endland and the aft endland contained within the nozzle jacket.