Vacuum insulated blast tube

Patent metadata

Field	Value
Publication number	US-12372049-B2
Application number	US-202318471908-A
Country	US
Kind code	B2
Filing date	Sep 21, 2023
Priority date	Sep 21, 2023
Publication date	Jul 29, 2025
Grant date	Jul 29, 2025

Abstract

A vacuum insulated blast tube includes an insulating layer of a burn resistant material such as phenolic resin formed on an interior surface of the blast tube to provide the necessary erosion and thermal insulation properties to protect the blast tube and a vacuum insulated layer formed in the walls of the blast tube itself to provide the additional thermal insulation properties to protect any non-propulsive sub-systems positioned in the void space around the blast tube. A void space in the walls of the blast tube is held under vacuum with a pressure of less than 25 Torr and a thermal conductivity Tcond_vac of less than one-third of the thermal conductivity of air Tcond_air to form the vacuum insulation layer.

First claim

We claim:

1. A vacuum insulated blast tube, comprising:
a hollow blast tube shell defining a void space therein along a length of the hollow blast tube shell; and
an insulating layer formed of a burn resistant material on an interior surface of the hollow blast tube shell,
wherein the void space is held under vacuum with a pressure of less than 25 Torr and a thermal conductivity (Tcond_vac) of less than one-third of a thermal conductivity of air (Tcond_air) to form a vacuum insulation layer, and
wherein an upstream end of the vacuum insulated blast tube connects to a downstream end of a combustion chamber of a rocket motor to receive hot gases from the combustion chamber and discharge the hot gases into a nozzle of the rocket motor.

2. The vacuum insulated blast tube of claim 1 , wherein the pressure in the void space is a medium vacuum between 25 Torr and 10 −3 Torr.

3. The vacuum insulated blast tube of claim 1 , wherein the pressure in the void space is a high vacuum between 10 −3 Torr and 10 −6 Torr.

4. The vacuum insulated blast tuber of claim 1 , wherein Tcond_vac is less than one-fifth Tcond_air.

5. The vacuum insulated blast tube of claim 1 , wherein Tcond_vac is approximately 1/6.6 that of Tcond_air.

6. The vacuum insulated blast tube of claim 1 , wherein Tcond_vac is less than one one-hundredth a thermal conductivity of the burn resistant material.

7. The vacuum insulated blast tube of claim 1 , wherein the burn resistant material erodes as the hot gases pass through the vacuum insulated blast tube and protects the vacuum insulated blast tube from elevated temperatures of the hot gases passing therethrough due to combustion of propellant, wherein the vacuum insulation layer provides additional thermal insulation to achieve a total thermal insulation.

8. The vacuum insulated blast tube of claim 1 , wherein the burn resistant material comprises a phenolic resin.

9. A vacuum insulated blast tube, comprising:
a hollow blast tube shell defining a void space therein along a length of the hollow blast tube shell; and
an insulating layer of phenolic resin having a thermal conductivity (Tcond_phenolic) on an interior surface of the hollow blast tube shell,
wherein the void space is held under vacuum with a pressure of less than 103 Torr and a thermal conductivity (Tcond_vac) of less than one-fifth of a thermal conductivity of air (Tcond_air) to form a vacuum insulation layer, wherein Tcond_vac is less than one-two hundredth of Tcond_phenolic, and
wherein an upstream end of the vacuum insulated blast tube connects to a downstream end of a combustion chamber of a rocket motor to receive hot gases from the combustion chamber and discharge the hot gases into a nozzle of the rocket motor.

10. The vacuum insulated blast tube of claim 9 , wherein the insulating layer erodes as the hot gases pass through the vacuum insulated blast tube and protects the vacuum insulated blast tube from elevated temperatures of the hot gases passing therethrough due to the combustion of propellant, wherein the vacuum insulation layer provides additional thermal insulation to achieve a total thermal insulation.

11. A rocket motor, comprising:
a cylindrical rocket motor casing having a diameter D 1 ;
a combustion chamber including a propellant positioned in the cylindrical rocket motor casing;
a nozzle positioned aft of the combustion chamber to expel hot gases resulting from combustion of the propellant;
a vacuum-insulated blast tube that couples the combustion chamber to the nozzle, said vacuum-insulated blast tube having a diameter D 2 <D 1 that defines a first void space between the vacuum-insulated blast tube and the cylindrical rocket motor casing;
one or more sub-systems positioned in the first void space, wherein the vacuum-insulated blast tube comprises:
a hollow blast tube shell defining a second void space therein along a length of the hollow blast tube shell; and
an insulating layer formed of a burn resistant material on an interior surface of the hollow blast tube shell that erodes as hot gases pass through the vacuum-insulated blast tube and protects the vacuum-insulated blast tube from elevated temperatures,
wherein the second void space is held under vacuum with a pressure of less than 25 Tom and a thermal conductivity (Tcond_vac) of less than one-third of a thermal conductivity of air (Tcond_air) to form a vacuum insulation layer to provide additional thermal insulation to thermally insulate the one or more sub-systems, and
wherein an upstream end of the vacuum-insulated blast tube connects to a downstream end of the combustion chamber to receive the hot gases from the combustion chamber and discharge the hot gases into the nozzle.

12. The rocket motor of claim 11 , wherein the pressure in the second void space is a medium vacuum between 25 Torr and 10 −3 Torr.

13. The rocket motor of claim 11 , wherein the pressure in the second void space is a high vacuum between 10 −3 Torr and 10 −6 Torr.

14. The rocket motor of claim 11 , wherein Tcond_vac is less than one-fifth Tcond_air.

15. The rocket motor of claim 11 , wherein the burn resistant material comprises a phenolic resin.

16. The rocket motor of claim 11 , wherein the burn resistant material erodes as the hot gases pass through the vacuum-insulated blast tube and protects the vacuum-insulated blast tube from elevated temperatures of the hot gases passing therethrough, wherein the additional thermal insulation achieves a total thermal insulation to protect the one or more sub-systems.

17. The rocket motor of claim 11 , wherein the burn resistant material comprises a phenolic resin.

Assignees

• Raytheon Co

Inventors

• Rascon John
• Formica Anthony V
• Leach John Regis

Classifications

• F02K9/40

  Cooling arrangements {(for nozzles F02K9/972)} · CPC title

• F02K9/346

  Liners, e.g. inhibitors · CPC title

• F02K9/34 Primary

  Casings; Combustion chambers; Liners thereof · CPC title

• F42B15/34 Primary

  Protection against overheating or radiation, e.g. heat shields; Additional cooling arrangements {(thermal protection fitted in or to cosmonautic vehicles B64G1/58)} · CPC title