Thrust control and sound suppression apparatus专利检索-空气动力学物理专利检索查询-专利查询网

Thrust control and sound suppression apparatus

阅读：165发布：2023-11-03

专利汇可以提供Thrust control and sound suppression apparatus专利检索，专利查询，专利分析的服务。并且Engine of either turbo fan or turbojet type is provided with multiple lobed exhaust nozzle. An ejector barrel defining a mixing zone is adapted to be connected at its leading edge to the lobe tips adjacent to the nozzle exit plane to receive engine gases and free stream air. A plenum chamber in the forward portion of the barrel has inlet ports in flow communication with tip portions of lobes, and guide vanes extend forward into lobes to split the mixed engine gases and guide outer streams into plenum chamber inlet ports while inner streams flow directly to mixing zone. An annular control nozzle at aft end of plenum chamber discharges high pressure gases into intermediate section of mixing zone to form a gaseous ring surrounding the other gases. The high velocity flow at inner wall increases total flow and makes velocity profile more uniform, and further mixing with adjacent gases reduced sound level. Design of control nozzle determines profile of gaseous ring which becomes virtual aerodynamic profile of aft portion of ejector barrel, which may be convergent-divergent nozzle shape for optimum cruise conditions of a high subsonic aircraft. Nozzle may also be adjustable to produce varying profiles for varying flight regimes. Basic design makes it possible to incorporate thrust reverser in aft portion of ejector barrel.，下面是Thrust control and sound suppression apparatus专利的具体信息内容。

权利要求

1. Apparatus for controlling the thrust and suppressing the sound of a jet engine, comprising: a nozzle connected to the aft end of the engine to receive high pressure Gases therefrom and discharge them rearwardly; the nozzle having a generally annular forward end for connection to the engine and being formed with a plurality of peripherally spaced axially and radially extending lobes forming rearward flow paths for the engine gases; the lobes defining between them a plurality of rearwardly converging valleys forming flow paths for the influx of free stream air to join the engine gases at the nozzle exit plane; and a generally annular ejector barrel having inner and outer walls and a leading edge and a trailing edge, and attached at its leading edge to the outer tips of the lobes substantially at the nozzle exit plane; the inner wall of the ejector barrel defining a mixing zone to receive and control the engine gases and free stream air; a generally annular plenum chamber formed between the inner and outer walls of the forward portion of the ejector barrel; inlet ports in the forward edge of the plenum chamber in flow communication with the radially outer tip ends of the lobes to receive portions of the engine gases; and rearwardly directed control nozzle means at the aft end of the plenum chamber at a locus intermediate the ends of the ejector barrel extending substantially around the periphery of the inner wall of the ejector barrel to discharge a ring of high pressure gases surrounding the mixture of free stream air and engine gases issuing from the engine nozzle and aerodynamically defining the effective profile of the aft portion of the inner wall of the ejector.

2. Apparatus as claimed in claim 1; and guide vanes extending into the aft ends of the lobes near their radially outer portions to divide the gaseous streams in the lobes and guide the outer portions of the streams into the inlet ports of the plenum chamber.

3. Apparatus as claimed in claim 2; in which the guide vanes comprise forward continuations of portions of the inner wall of the plenum chamber.

4. Apparatus as claimed in claim 3; in which the forward edge of the plenum chamber is closed and streamlined in the areas between the lobes to confine the high pressure gases in the plenum chamber and to reduce resistance to external air flow.

5. Apparatus as claimed in claim 1; in which the inner wall of the plenum chamber comprises a substantially cylindrical ring forming the inner wall of the forward portion of the ejector barrel; peripherally spaced portions of the ring extend forwardly into the aft portions of the lobes to serve as guide vanes dividing the flows and directing the radially outer portions into the inlet ports of the plenum chamber; and the peripherally spaced intermediate portions of the ring are reversely curved to close the forward edge of the plenum chamber between the lobes and their free ends are secured to the outer wall of the ejector barrel.

6. Apparatus as claimed in claim 1; and means to control the flow of high pressure gases from the plenum chamber into the mixing zone.

7. Apparatus as claimed in claim 6; in which the flow control means comprises a ring forming the forward marginal edge of the control nozzle means; the ring being axially movable to vary the area and effective shape of the control nozzle opening.

8. Apparatus as claimed in claim 1; the engine including a turbine discharge opening and a fan air discharge opening both exhausting into the engine nozzle to cause mixing of the fan air and turbine gases in the lobes prior to discharge into the mixing zone of the ejector barrel.

9. Apparatus as claimed in claim 1; including passages in the aft portion of the ejector barrel extending through its inner and outer walls; and a blocker door pivotally mounted in each passage on a transverse axis; the doors being swingable rearward and inward toward each other to block rearward flow of the gases from the mixing zone and divert them laterally out through the passages to produce reverse thrust.

10. Thrust controlling and sound suppressing apparatus for use in combination with a jet engine having an exhaust nozzle formed With peripherally spaced lobes defining between them valleys for influx of free stream air, comprising: an ejector barrel having inner and outer walls and leading and trailing edges; the inner wall defining a mixing zone for engine gases and free stream air; the leading edge of the ejector barrel being adapted to be connected to the outer tips of the lobes to provide for inflow of free stream air; a plenum chamber in the forward portion of the ejector barrel having forward opening inlet ports adapted for flow communication with the radially outer portions of the lobes; and guide vanes carried by the ejector barrel to extend into the lobes and divide the gases into outer streams flowing into the inlet ports and inner streams flowing directly into the mixing zone; and a substantially annular control nozzle at the aft end of the plenum chamber to exhaust gases therefrom into the mixing zone in a ring surrounding the mixed gases.

11. Apparatus as claimed in claim 10; including passages in the aft portion of the ejector barrel extending through its inner and outer walls; and a blocker door pivotally mounted in each passage on a transverse axis; the doors being swingable rearward and inward toward each other to block rearward flow of the gases from the mixing zone and divert them laterally out through the passages to produce reverse thrust.

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Thrust control and sound suppression apparatus

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