FIELD: engines and pumps.
SUBSTANCE: flame stabiliser for augmenter of bypass turbojet including first and second circular inner circuits 3, 5. Primary flow passage 4 is arranged there between. Outer circular circuit 2 and first inner circular circuit 3 makes passage 1 for secondary flow. Besides, it comprises at least one support of strut 8 made from metal for attachment to said outer circular circuit 2 by top plate 9 and at least one flame stabiliser strut 7. Said flame stabiliser strut 7 features monoblock structure of composite and is composed of two rigidly interconnected walls 28a, 28b arranged to make a neck with V-shape profile. Top parts 31a, 31b of said walls located in secondary flow have means 34a, 34b for attachment to strut support 8. Top parts 31a, 31b of said walls are flat and opposed.
EFFECT: perfected design.
17 cl, 7 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| FLAME STABILIZER | 2016 |
|
RU2700815C2 |
| FUEL FEED UNIT TO THE BYPASS TURBOJET ENGINE AFTERBURNER | 2015 |
|
RU2614268C1 |
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|
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|
SU702758A1 |
| AFTERBURNER OF DOUBLE-FLOW JET TURBINE ENGINE, DOUBLE-FLOW JET TURBINE ENGINE AND BRACKET OF FLAME STABILISER FOR AFTERBURNER | 2007 |
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| DEVICE AND METHOD (VERSIONS) TO STABILISE FLAME IN TURBOJET ENGINE AFTERBURNER CHAMBER | 2009 |
|
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| REHEAT RING FOR DOUBLE-FLOW TURBOJET ENGINE, REHEAT DEVICE AND TURBOJET ENGINE | 2004 |
|
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|
RU2680781C1 |
| AFTERBURNER OF BY-PASS TURBOJET ENGINE | 0 |
|
SU928869A2 |
