Thrust nozzle of turbojet engines
阅读：329发布：2022-12-04
专利汇可以提供Thrust nozzle of turbojet engines专利检索，专利查询，专利分析的服务。并且A thrust nozzle at a tapering fuselage or nacelle tail section of an aircraft which is located downstream and adjoins an afterburner tailpipe of a turbojet engine, the exhaust gas discharge cross section of the nozzle can be adjusted by means of nozzle flaps which are pivotal about axes disposed transversely to the flow direction of the engine exhaust gases; the flaps are adapted to be actuated by an axially displaceable shroud which includes one or more tapering sections adapted to be extended out of the engine cowling for increasing the exhaust gas discharge cross section, to engage in recesses provided in the nozzle flaps.，下面是Thrust nozzle of turbojet engines专利的具体信息内容。
1. A thrust nozzle arranged at a tapering fuselage or nacelle tail section of an aircraft and adjoining an afterburner tailpipe of a turbojet engine, the exhaust gas discharge cross section of said nozzle being adjustable by means of nozzle flap means pivotal about axes disposed substantially transversely to the flow direction of the engine exhaust gases, and which comprises flap-actuating means for actuating said flap means including an axially displaceable nozzle-actuating shroud means, characterized in that, for increasing the exhaust gas discharge cross section of the thrust nozzle, at least one tapering section of the nozzle-actuating shroud means is operable to be extended out of the engine cowling associated with the fuselage or nacelle tail section to engage downstream in recesses provided in the nozzle flap means, and the pivot bearing means for the nozzle flap means located within the engine cowling as well as within the nozzleactuating shroud means.
2. A thrust nozzle according to claim 1, characterized in that the taper of each tapering section of the nozzle-actuating shroud means substantially follows the taper of the fuselage or nacelle tail section.
3. A thrust nozzle according to claim 2, characterized in that each section of the nozzle-actuating shroud means tapers substantially conically.
4. A thrust nozzle according to claim 3, characterized in that the fuselage or nacelle tail section tapers substantially uniformly.
5. A thrust nozzle according to claim 1, characterized in that several tapering sections of the nozzle-actuating shroud means are provided.
6. A thrust nozzle according to claim 5, characterized in that, in the position of the smallest exhaust gas discharge cross section of the thrust nozzle, the inner sliding surfaces provided on the flap means which, for the engagement of each tapering section of the shroud means, are associated with the recesses of the flap means, are inclined more strongly toward the inside in deviation from the conicity of the shroud means.
7. A thrust nozzle according to claim 6, characterized in that the downstream sections of the actuating shroud means are displaceable over rollers supported on the nozzle flap means.
8. A thrust nozzle according to claim 7, characterized in that the nozzle flap means are provided with heat shield means at their inner surfaces, which as a continuation of heat shield means associated with an afterburner tailpipe as well as of a coolant duct, are adapted to be subjected to cooling air in each end position of the nozzle flap means.
9. A thrust nozzle according to claim 8, characterized in that the taper of each tapering section of the nozzle-actuating shroud means substantially follows the taper of the fuselage or nacelle tail section.
10. A thrust nozzle according to claim 9, characterized in that each section of the nozzle-actuating shroud means tapers substantially conically.
11. A thrust nozzle according to claim 10, characterized in that the fuselage or nacelle tail section tapers substantially uniformly.
12. A thrust nozzle according to claim 1, characterized in that, in the position of the smallest exhaust gas discharge cross section of the thrust nozzle, the inner sliding surfaces provided on the flap means which, for the engagement of each tapering section of the shroud means, are associatEd with the recesses of the flap means, are inclined more strongly toward the inside in deviation from the conicity of the shroud means.
13. A thrust nozzle according to claim 1, characterized in that the downstream sections of the actuating shroud means are displaceable over rollers supported on the nozzle flap means.
14. A thrust nozzle according to claim 1, characterized in that the nozzle flap means are provided with heat shield means at their inner surfaces, which as a continuation of heat shield means associated with an afterburner tailpipe as well as of a coolant duct, are adapted to be subjected to cooling air in each end position of the nozzle flap means.
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