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Regeneratively cooled porous media jacket

A porous medium, cooling technology, applied in the direction of machine/engine, engine function, rocket engine device, etc., can solve the problem of not being able to provide proper cooling

Inactive Publication Date: 2012-01-04
FIRESTAR ENG
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Existing cooling means do not provide proper cooling during and / or after engine operation

Method used

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  • Regeneratively cooled porous media jacket
  • Regeneratively cooled porous media jacket
  • Regeneratively cooled porous media jacket

Examples

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Effect test

example 1

[0042] Example 1 - Lithographic method

[0043] exist Figure 5 The photolithographic fabrication method is outlined in . In the stacked and bonded lithographic fabrication method, a limited number of layers are fabricated which when stacked and bonded (along the axis of the engine) make up the combustion chamber, porous media passages, and pressure shell ) (in order from the inside of the engine to the outside of the engine). Along the thrust axis of the propeller, the chamber profile varies to impede flow through the throat region and to expand flow through the expansion nozzle to generate thrust.

[0044] The internal dimensions of the porous media vary to conform to the combustion chamber profile and the outer diameter of the porous media will vary to control the jacket gap and microfluidic geometry to minimize pressure drop across the jacket Control cooling. A three-dimensional porous media sheath is built in stacked layers and is typically fusion bonded (with appli...

example 2

[0058] Example 2 - Processing metal foam

[0059] refer to Figure 6 An alternative method of fabricating a regeneratively cooled porous media jacket, including machining and assembly, is described. This manufacturing method relies on more traditional mechanical design and manufacturing methods. Initially, the unassembled jacket is in the form of separate parts: inner wall 600 (which defines the combustion chamber), two halves of porous media 602 and 604 , and two halves of outer walls 606 and 608 . Candidate materials for inner wall 600 include, but are not limited to, copper, aluminum, nickel, nickel alloys, stainless steel, niobium, rhenium, tantalum, molybdenum, carbon, carbon-carbon composites, or alloys / combinations thereof. Materials with higher thermal conductivity are advantageous for certain applications; however, the chamber material is selected for the desired combustion process. Not all materials can be manufactured with conventional machining, so use appropr...

example 3

[0070] Example 3 - Model for the design of a regeneratively cooled jacket

[0071] Disclosed herein is a system-level analytical fluid model for the inclusion of a porous media within a regeneratively cooled rocket combustion chamber jacket for the purpose of representing the porous media in this type of application to allow rocket thrusters to The ability of a gas phase propellant to function. In this example, the specific design problems of typically worst-case (in terms of cooling and jacket pressure drop capabilities) gas-phase NOFB unit propellant rocket motors are addressed, although it is also possible to address different types of motors on the basis of these teachings . Further details of NOFB unit propellants can be found in the already incorporated US Patent Application No. 12 / 268,266.

[0072] Typically, the thermal conductivity of the fluid limits the heat transfer into the regeneratively cooled combustion chamber. This then limits the cooling ability of the ...

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Abstract

The fluid and heat transfer theory for regenerative cooling of a rocket combustion chamber with a porous media coolant jacket is presented. This model is used to design a regeneratively cooled rocket or other high temperature engine cooling jacket. Cooling jackets comprising impermeable inner and outer walls, and porous media channels are disclosed. Also disclosed are porous media coolant jackets with additional structures designed to transfer heat directly from the inner wall to the outer wall, and structures designed to direct movement of the coolant fluid from the inner wall to the outer wall. Methods of making such jackets are also disclosed.

Description

[0001] Inventors: Greg Mungas, David Fisher, Jack Merrill Fryer, and Adam Pollok London London) [0002] Cross-references to related applications [0003] This application claims the benefit of priority to U.S. Provisional Patent Application No. 61 / 120,776, entitled "Regeneratively Cooled Porous Media Jacket," filed December 8, 2008, and in particular, to The entire contents of its disclosure or teaching are hereby incorporated by reference. [0004] This technology was funded in part by NASA contract NNX09CB12C administered by NASA / Shared Services Center. The United States Government may have certain rights in this invention. Background technique [0005] Research in rocketry has led to many improvements in rocket motor, propellant, and propulsion design. However, at least one question remains. Rocket engines produce high temperature combustion gases and a large heat release during operation. Designing materials, structures, and cooling methods to withstand such extreme...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/40F02K9/34F02K9/62F02K9/64
CPCF05D2260/20F02K9/34F02K9/00F02K9/40F02K9/64F02K9/972Y10T29/49346
Inventor 格雷格·蒙加斯戴维·J·费希尔阿达姆·波洛克·伦敦杰克·梅里尔·弗赖尔
Owner FIRESTAR ENG
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