发明名称 |
GAS-TURBINE ENGINE REACTIVE JET SILENCER |
摘要 |
FIELD: civil and transport aviation; devices with high-velocity gas or liquid jets which are main source of noise. SUBSTANCE: silencer is located at exit section of reaction nozzle. It includes foam generating liquid supply branch pipe 1, foam generating chamber made in form of recess 2 and guide deflector 3. Walls of recess are profiled to lines of flow of potential vortex. Front wall of recess is connected with sharp edge 4 of planar or axisymmetrical nozzle 5 of gas-turbine engine. Supply branch pipe is provided with manifold 6 located on rear wall of recess. EFFECT: reduced overall dimensions and simplified construction. 2 cl, 1 dwgn
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申请公布号 |
RU2105894(C1) |
申请公布日期 |
1998.02.27 |
申请号 |
RU19960109277 |
申请日期 |
1996.05.05 |
申请人 |
KAZANSKIJ GOSUDARSTVENNYJ TEKHNICHESKIJ UNIVERSITE;T IM A N TUPOLEVA |
发明人 |
VARSEGOV V.L.;FRANOV A.N.;KOSTERIN V.A.;KHABIBULLIN M.G.;TORBIN V.M.;NASYROV S.R.;PODSHIVALIN A.V.;ZELENOV E.S.;ROGOV V.I.;VARSEGOV V.L.;FRANOV A.N.;KOSTERIN V.A.;KHABIBULLIN M.G.;TORBIN V.M.;NASYROV S.R.;PODSHIVALIN A.V.;ZELENOV E.S.;ROGOV V.I. |
分类号 |
F02K1/34;(IPC1-7):F02K1/34 |
主分类号 |
F02K1/34 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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