JP2000230882A - Semifree-jet testing apparatus - Google Patents

Abstract

PROBLEM TO BE SOLVED: To lower the back pressure of a supersonic nozzle and to enhance a starting property without making the capacity and the size of a pump or an exhauster large. SOLUTION: In this semifree-jet testing apparatus, a supersonic diffuser 6 is connected to the exit part 2b of a supersonic nozzle 2 which takes into a supersonic airflow, The extrance part 10a of a subsonic diffuser 10 is made to communicate with the exit part of the supersonic diffuser 6. A turbo-engine 11 is connected to the exit part 10b of the subsonic diffuser 10. A cowl external bypass part 14 is formed on the side of a cowl 7a which becomes the surface of the supersonic diffuser 6. A cowl external bypass part 15 which changes the opening area of the cowl external bypass part 14 is equipped at the part.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a semi-free jet test apparatus used for performing a matching test with a turbo engine by sucking a supersonic airflow with a supersonic intake.

[0002]

2. Description of the Related Art In a supersonic propulsion engine, it is an important technical problem to integrate a supersonic airflow with a supersonic intake and to perform a test on matching with a turbo engine.

[0003] In order to perform the above test on the ground, a semi-free jet test apparatus is required. FIG. 5 schematically shows an example of such a case, in which a cowl outer surface bypass portion c is communicated with an outlet portion (rear end portion) of a supersonic nozzle a via a supersonic diffuser b, and an outlet of the supersonic diffuser b is provided. The outlet (rear end) is connected to the inlet (tip) of a subsonic diffuser e having an outlet (rear end) connected to the turbo engine d, and the junction between the outlet of the supersonic diffuser b and the subsonic diffuser e is connected. An opening is formed in the throat bleed portion f on the lamp side of the portion, and a duct g is provided in the throat bleed portion f.

In such a semi-free jet test apparatus, when driving a turbo engine d, a supersonic nozzle a
A part of the supersonic airflow taken in is sucked in by the cowl outer surface bypass portion c, and the remaining airflow is reduced to a subsonic speed by the subsonic diffuser e and guided to the turbo engine d.
At the time of starting, a large back pressure acts on the supersonic nozzle a. Therefore, a method of forcibly starting the cowl by pulling the cowl outer surface bypass part c to a low pressure or a method of pulling the low pressure chamber to a sufficiently low pressure is adopted. are doing.

[0005]

However, in order to prevent the back pressure from acting on the supersonic nozzle a by pulling the cowl outer surface bypass portion c to a sufficiently low pressure to the starting level so that a large back pressure does not act on the supersonic nozzle a, the pump or the pump having a large capacity or size is required. An exhaust fan is required.

Therefore, the present invention is intended to improve the startability by reducing the back pressure of the supersonic nozzle without using a pump or exhaust fan having a large capacity and size. Things.

[0007]

SUMMARY OF THE INVENTION In order to solve the above-mentioned problems, according to the present invention, a supersonic diffuser is joined to an outlet of a supersonic nozzle, and a supersonic diffuser is connected to a turbo engine at an outlet of the supersonic diffuser. In the semi-free jet test apparatus in which the subsonic diffuser is connected in communication and the cowl side of the supersonic diffuser portion has a cowl outer surface bypass portion, the opening area of the cowl outer surface bypass portion can be adjusted. The cowl exterior bypass device is equipped.

When the opening area of the cowl outer surface bypass portion is increased by the cowl outer surface bypass device at the time of starting, the back pressure acting on the supersonic nozzle is reduced, so that the startability can be improved.

Further, the cowl outer surface bypass device comprises a flap in which the opening area of the cowl outer surface bypass portion is changed by a vertical rotation about a hinge, and an actuator for rotating the flap. By doing so, reliable operation can be obtained with a simple configuration.

[0010]

Embodiments of the present invention will be described below with reference to the drawings.

FIGS. 1 to 4 show an embodiment of the present invention. The inlet 1a of a cylindrical casing 1 having one end in the longitudinal direction as an inlet 1a and the other end as an outlet 1b. Side, the supersonic nozzle 2 is installed, the inlet 2a of the supersonic nozzle 2 is connected to the inlet 1a of the casing 1 via the connection adapter 3, and the supersonic nozzle 2 A bleed tube 5 led from a supersonic nozzle bleed device 4 installed outside the casing 1 is connected to the outlet 2b side, and a supersonic diffuser 6 as a supersonic intake is connected.

An outlet 10a of the subsonic diffuser 10 is connected to an outlet of the supersonic diffuser 6, and an outlet 10b of the subsonic diffuser 10 is connected to the turbo engine 11, the flexible duct 12, and the bypass valve controller. A cowl outer surface bypass portion 14 is formed on the cowl 7a side of a portion where the throat bleed portion 7 is joined to the outlet of the supersonic diffuser 6.

In the semi-free jet test apparatus having the above configuration, a cowl outer surface bypass device 15 which is a feature of the present invention is provided.

The cowl outer surface bypass device 15 is shown in FIG.
4 and FIG. That is,
On the cowl 7a side, which is the upper surface side of the supersonic diffuser 6,
The hinge 16 is positioned close to the outlet 2b of the supersonic nozzle 2 so that the opening area of the cowl outer surface bypass portion 14 can be adjusted to be large or small by turning the hinge 16 as a fulcrum in the vertical direction. In order to assemble and adjust the rotation of the flap 17
The arm 18 extends over the upper surface of the supersonic nozzle 7, and a rod 19 of a servo cylinder 19 as an actuator disposed above the supersonic nozzle 2 is provided at the tip of the arm 18.
a is connected via a connecting link 20 so that the arm 18 is pushed and pulled by the servo cylinder 19 so that the flap 17 can be opened and closed.
The stopper 21 for regulating the lowering position of the arm 7
8, the stopper 21 is held by a stopper receiver 22 projecting from the outer surface of the outlet 2b of the supersonic nozzle 2.

1 to 4, 9 is a throat bleed duct, 23 is a supersonic nozzle frame, 24 is a supersonic diffuser frame, and 25 is a schlieren window provided on the side surface of the cowl 7a of the supersonic diffuser 6. Glass, 26
Denotes an intake bleed controller, 27 denotes a turbo engine mount, and 28 denotes a cooling duct.

When the turbo engine 11 is driven, the supersonic nozzle bleeding device 4 is operated to take in the supersonic airflow by the supersonic nozzle 2 and a part of the taken supersonic airflow is sucked by the cowl outer surface bypass portion 14. The airflow guided to the turbo engine 11 through the subsonic diffuser 10 is reduced to a subsonic speed. At the start, the cowl external bypass device 15 is operated by operating the cowl external bypass device 15.
To increase the opening area.

In the above case, when the servo cylinder 19 is operated to retract the rod 19a, the rod 1
Flap 1 connected to connecting line 9a via connecting link 20
7 will be pulled toward the supersonic nozzle 2 side. For this reason, the flap 17 which normally holds the cowl outer surface bypass portion 14 at a required opening area at the position indicated by the solid line in FIG. 3 is rotated upward as shown by the two-dot chain line. The opening area of the cowl outer surface bypass portion 14 is enlarged. As a result, the back pressure of the supersonic nozzle 2 can be reduced without using a pump or an exhaust fan having a large capacity and size as in the related art, so that the startability can be improved. At this time, the cowl outer surface bypass portion 14
When the opening area is sufficiently larger than the throat area of the supersonic nozzle 2, the swallowing function (swallow function) can be made 1 or more, and the startability can be further improved.

Also, in the case where the suction into the supersonic diffuser 6 and the subsonic diffuser 10 is not performed during the above test, the opening area of the cowl outer surface bypass portion 14 can be increased to prevent the start-up and the non-start operation. The impact load generated at the time of buzz can be reduced, and the influence on the entire device can be reduced.

In the above, the cowl outer surface bypass device 1
5 has a structure in which the flap 17 is rotated by the operation of the servo cylinder 19, so that it is possible to obtain a strength with respect to the supersonic airflow and a reliable operation with a simple structure.

It should be noted that the present invention is not limited to the above-described embodiment, and the cowl outer surface bypass device 15 may be configured such that a member such as a valve body is moved closer to or away from the cowl outer surface bypass portion, or the gate is closed. It is needless to say that such a structure as to slide the member can be arbitrarily adopted, and various changes can be made without departing from the gist of the present invention.

[0021]

As described above, according to the semi-free jet test apparatus of the present invention, the following excellent effects are exhibited. (1) At the outlet of the supersonic nozzle, a supersonic diffuser is joined, and at the outlet of the supersonic diffuser, a subsonic diffuser connected to a turbo engine is connected and connected, and the cowl side of the supersonic diffuser portion. In addition, in the semi-free jet test apparatus in which the cowl outer surface bypass portion is formed, the cowl outer surface bypass device is provided so that the opening area of the cowl outer surface bypass portion can be adjusted. By increasing the opening area of the cowl outer bypass section with the outer bypass device, the back pressure of the supersonic nozzle can be reduced without using a large-capacity, large-sized pump or exhaust fan, and the startability can be improved. it can. (2) The cowl outer surface bypass device is configured to include a flap configured to change the opening area of the cowl outer surface bypass portion by turning the hinge up and down in a vertical direction, and an actuator that rotates the flap. Thus, with a simple structure, strength against supersonic airflow can be obtained, and reliable operation can be obtained.

[Brief description of the drawings]

FIG. 1 is a partially cut-away side view showing an embodiment of a semi-free jet test apparatus of the present invention.

FIG. 2 is a plan view of FIG.

FIG. 3 is an enlarged view taken on line AA of FIG. 2;

FIG. 4 is a plan view of FIG. 3;

FIG. 5 is a schematic view showing an example of a conventional semi-free jet test apparatus.

[Explanation of symbols]

 2 supersonic nozzle 2b outlet 6 supersonic diffuser 7a cowl 10 subsonic diffuser 11 turbo engine 14 cowl outer surface bypass section 15 cowl outer surface bypass device 16 hinge 17 flap 19 servo cylinder (actuator)

 ──────────────────────────────────────────────────続 き Continuing on the front page (72) Inventor Kanji Itahara 3-5-1 Mukodai-cho, Tanashi-shi, Tokyo Ishikawa Shima-Harima Heavy Industries Co., Ltd. Tanashi Plant (72) Inventor Ryoji Yanagi 6, Minami-Oizumi 6, Nerima-ku, Tokyo -11-6 F term (reference) 2G023 AB22 AC10 AD01 2G087 AA04 BB26 BB40 CC13 CC29 EE11

Claims (2)

[Claims] A supersonic diffuser is joined to an outlet of a supersonic nozzle, and a subsonic diffuser connected to a turbo engine is connected to an outlet of the supersonic diffuser, and a supersonic diffuser is connected to the supersonic diffuser. A semi-free jet test apparatus in which a cowl outer surface bypass portion is formed on the cowl side, wherein the cowl outer surface bypass device is configured to be equipped with a cowl outer surface bypass device capable of adjusting an opening area of the cowl outer surface bypass portion. Semi-free jet test equipment. 2. A cowl outer surface bypass device comprising: a flap configured to change an opening area of the cowl outer surface bypass portion by a vertical rotation about a hinge as a fulcrum; and an actuator configured to rotate the flap. The semi-free jet test apparatus according to claim 1, wherein