Fuel system and method for supplying a combustion chamber in an aircraft turboshaft engine with fuel
US-2024318601-A1 · Sep 26, 2024 · US
US9470420B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-9470420-B2 |
| Application number | US-201013387939-A |
| Country | US |
| Kind code | B2 |
| Filing date | Jul 21, 2010 |
| Priority date | Aug 3, 2009 |
| Publication date | Oct 18, 2016 |
| Grant date | Oct 18, 2016 |
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Counterflow burner having a combustion chamber ( 5 ) to which combustible gas (B) and an oxidising agent ( 0 ) can be fed from opposite sides, having three planar substrates ( 1, 2, 3 ) which are interconnected, lying one above the other, the middle substrate ( 2 ) having the combustion chamber ( 5 ), from which passages ( 4 ), lying in the plane of the substrate, lead to the edge, the upper substrate ( 3 ) and the lower substrate ( 1 ) being closed, and at least the middle substrate ( 2 ) is produced using methods of microsystem technology.
Opening claim text (preview).
The invention claimed is: 1. Counterflow burner comprising: a combustion chamber ( 5 ) and passages ( 4 ) for conveying a combustible gas (B) and an oxidizing agent gas ( 0 ) to the combustion chamber from different directions, having three planar substrates ( 1 , 2 , 3 ) which are interconnected, lying one above the other, the middle substrate ( 2 ) having the combustion chamber ( 5 ), from which the passages ( 4 ), lying in the plane of the middle substrate, lead in opposite directions to the edge of the substrate in a radial manner, and the combustible gas (B) and the oxidizing agent ( 0 ) introduced through the passages from opposite directions collide in the combustion chamber so two oxidizing agent gas streams and two combustible gas streams meet from exactly opposite directions and achieve a flame front having a spherical shape, and at least the middle substrate ( 2 ) being configured as a microsystem; wherein the upper substrate ( 3 ) and the lower substrate ( 1 ) are closed except for openings which are directed towards the combustion chamber and through which gas can enter or discharge perpendicularly to the plane of the substrates. 2. Counterflow burner according claim 1 , wherein the upper substrate ( 3 ) and/or the lower substrate ( 1 ) are, or is, also structured using methods of microsystem technology. 3. Counterflow burner according to claim 1 , wherein the middle substrate ( 2 ) consists of silicon. 4. Counterflow burner according to claim 1 , wherein the upper substrate ( 3 ) and/or the lower substrate ( 1 ) consist(s) of borosilicate glass. 5. Counterflow burner according to claim 1 , wherein flame stabilising elements ( 6 ) are applied to the upper substrate ( 3 ) and/or to the lower substrate ( 1 ). 6. Counterflow burner according to claim 1 , wherein the passages ( 4 ) are directed towards the middle point of the combustion chamber ( 5 ). 7. Counterflow burner according to claim 1 , wherein the passages ( 4 ) have different cross sections in the end region which is directed towards the combustion chamber ( 5 ). 8. Counterflow burner according to claim 1 , wherein the upper substrate ( 3 ) and/or the lower substrate ( 1 ) are, or is, coated in the region of the combustion chamber ( 5 ) with materials which accelerate combustion.
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