JPS63162955A - Nacelle housing type ejector - Google Patents

Abstract

PURPOSE:To make it possible to lower an air resistance during high speed cruising by forming the outer circumferential edge of a engine nacelle and the same of an ejector to be able to coincide with the beginning line of the moving locus of the ejector. CONSTITUTION:An ejector 2 is shifted to the beginning end of a moving locus to cover a nozzle portion 1a under retracted condition, to the rear of a nacelle outer circumferential edge of the ejector 2 coincides with the same of an engine nacelle 1 to form a smooth curve along both outer circumferences. Thereby, when an aircraft cruises at a high speed, the ejector 2 is shifted to the beginning end to be housed in the engine nacelle 1 side to be able to sharply reduce die air resistance. And the ejector 2 is shifted to the end of the moving locus to increase jet propulsive force, and the deflection of the propulsive force becomes possible if the ejector 2 is oscillated under this condition.

Description

Detailed Description of the Invention (Industrial Application Field) The present invention relates to an ejector for a turbine engine mounted on an aircraft, and in particular, to an ejector for a turbine engine mounted on an aircraft, and particularly for increasing and deflecting jet propulsive force and reducing air resistance during high-speed cruising. The present invention relates to a nacelle retractable ejector that can be suppressed.

(Prior Art) In order to increase the jet propulsion force of a turbine engine, it is generally known that an ejector is provided at the rear of the engine nacelle (see, for example, Japanese Patent Laid-Open No. 52-52016). This type of ejector is provided at the rear of the engine nacelle so as to be freely movable in the axial direction, and when increasing thrust, the ejector is pushed out to the rear of the nacelle.

On the other hand, some turbine engines are known in which a deflector is provided at the exhaust port of the exhaust nozzle in order to deflect the jet propulsive force (for example, see Japanese Utility Model Application No. 56-41436). In this type of jet, a deflector is swingably provided at the exhaust port, and the jet propulsion force is deflected by causing the exhaust gas to directly collide with the deflector.

(Problems to be Solved by the Invention) Hitherto, nothing has been proposed that combines both functions. Furthermore, the former has the disadvantage that air resistance increases when the ejector is housed in the engine nacelle and the aircraft is cruising at high speed. The latter has disadvantages in that engine exhaust directly collides with the deflector, which increases vibration, and also increases weight because the deflector must be strong in terms of heat resistance and strength.

It is an object of the present invention to solve the problems of the conventional techniques described above, to simultaneously increase jet propulsion force and deflection of the jet propulsion force, and to suppress air resistance during high-speed cruising. An object of the present invention is to provide a nacelle retractable ejector that enables the following.

(Means for Solving the Problems) In order to achieve the above object, the present invention includes an engine nacelle, an engine nacelle disposed on the same axis as the nacelle, movable in an axis and direction, and an end point of the locus of movement. and a swingable ejector, and is characterized in that the outer circumferential edge of the engine nacelle and the outer circumferential edge of the ejector are formed so that they can coincide at the starting end of the movement locus.

(Function) According to the present invention, if the ejector is moved to the end of the movement track, the jet propulsive force increases, and if the ejector is oscillated in this state, the propulsive force can be deflected. Furthermore, if the ejector is moved to the starting end of the moving track, the outer circumferential edges of the engine nacelle and the ejector coincide, reducing air resistance.

(Embodiment) Hereinafter, an embodiment of a nacelle retractable ejector according to the present invention will be described based on the accompanying drawings showing a longitudinal section of an engine.

In the figure, reference numeral 1 indicates an engine nacelle in which a nozzle portion 1a is formed at the rear thereof, and an ejector 2 is disposed on the same axis at the rear of the engine nacelle 1. The ejector 2 is movable in the axial direction, and when it is retracted backward, the ejector 2 is displaced so as to cover the nozzle part 1a at the starting end of the movement trajectory as shown in FIG. coincides with that of the engine nacelle 1, and a smooth curve is formed on the outer periphery of both.

When increasing the jet thrust of the engine, the ejector 2 is displaced to the end of its travel trajectory as shown in FIG. In this state, the engine exhaust gas 3 is accelerated inside the ejector 2, the static pressure inside the ejector 2 becomes lower than that of the outside air 4, and the secondary air 5 is sucked into the ejector 2. The secondary air 5 and the exhaust gas 3 are mixed to form a mixed exhaust gas 6, which is ejected to the rear of the ejector 2. Therefore, the jet propulsion force is increased compared to the case of only the exhaust gas 3 (FIG. 1).

On the other hand, when the aircraft is cruising at high speed, the ejector 2 is moved to the starting end as shown in FIG. 1 and stored on the engine nacelle 1 side. In this state, only the engine exhaust gas 3 is ejected to the rear of the ejector 2. In the conventional structure, when the engine nacelle 1 and the ejector 2 are overlapped, the outer peripheries of the two do not form a smooth curve, which increases air resistance.

According to the present invention, when the ejector 2 is displaced as shown in FIG. 1, the outer circumferential edges of the engine nacelle 1 and the ejector 2 coincide, forming a smooth curve.
Air resistance can be significantly reduced.

Further, after the ejector 2 according to the present invention is displaced to the terminal end, it can be freely photographed as shown in FIG. In this state, the mixed exhaust gas 6 of the engine exhaust gas 3 and the secondary air 5 is deflected inside the ejector 2 as shown in the figure and ejected rearward. As a result, the jet propulsion force is increased and, at the same time, an upward lift force F is imparted to the aircraft. It goes without saying that a downward force is applied to the aircraft depending on the direction in which the ejector 2 swings.

Next, another embodiment of the nacelle retractable ejector according to the present invention will be described with reference to FIGS. 4 to 6.

According to this embodiment, inside the ejector 2, there are segmented anti-nodal flow plates 7, 7 . ...7 are arranged radially. FIG. 4 shows the state during high-speed cruising, FIG. 5 shows the state in the middle of ejector extrusion, and FIG. 6 shows the state when changing the jet propulsion force.

With this configuration, when changing the jet propulsion force, the exhaust gas 3 of the engine is moved through the deflection plates 7, 7 as shown in FIG.
．． ...7, and the phenomenon of direct contact with the ejector 2 can be prevented. If a direct collision were to occur, the jet propulsion force would be reduced, vibration would increase, and the ejector would have to be designed with sufficient heat resistance and strength resistance to withstand the collision. Although the weight increases, according to this embodiment, it is possible to avoid the above-mentioned disadvantages. Note that the direction and magnitude of the jet propulsion force are determined by the drift plate 7.
,7. ...7. It goes without saying that the ejector 2 and the variable aperture ratio mechanism (not shown) are adjustable.

〔Effect of the invention〕

According to the present invention, with the above configuration, it is possible to simultaneously increase and deflect the jet propulsive force, and reduce air resistance during high-speed cruising.

[Brief explanation of the drawing]

1 to 3 are longitudinal sectional views showing one embodiment of a nacelle retractable ejector according to the present invention, and FIGS. 4 to 6 are longitudinal sectional views showing other embodiments of the same. 1...Engine nacelle, 2...Ejector, 3...
・Exhaust, 5...Secondary air, 6...Mixed exhaust. Applicant's agent Mr. Sato Figure 1 Figure 2 Figure 3 Figure 4 Figure 5 Figure 6

Claims (1)

[Scope of Claims] 1. Consisting of an engine nacelle and an ejector disposed on the same axis as the nacelle, movable in the axial direction, and swingable at the end of its movement trajectory; A nacelle retractable ejector, characterized in that a peripheral edge and an outer peripheral edge of the ejector are formed so that they can coincide at a starting end of the movement trajectory. 2. The nacelle retractable ejector according to claim 1, further comprising a deflection plate that can deflect the engine exhaust gas at the end of the movement trajectory inside the ejector.