Afterburner chamber air-jet engine


F23R3/22 - movable, e.g. to an inoperative position; adjustable, e.g. self-adjusting

 

Afterburner chamber air-jet engine includes an outer wall with split housings and heat shields, the fuel manifold, the front of the device with the radial stabilizers, flame, evenly spaced around the circumference of the gas flow duct. The stabilizers have the ability to rotate along the axis of the camera by means of the drive mechanism, made in the form of a hydraulic cylinder. A hydraulic cylinder pivotally attached to the rear flange of the outer wall. The outer wall and middle parts of the stabilizers supplied brackets. The outer wall brackets pivotally connected with the outer ends of the stabilizers. The brackets of the middle part of stabilizers pivotally connected with adjustable thrust. The second end of the traction connected with duplechin lever, which, in turn, is connected to a rod of the hydraulic cylinder. Axis duplicera lever is made with a bore cylindrical necks, bearing on the outer side of the side brackets and paired on lehlohonolo landing with holes made in split housings of the exterior wall. The invention allows to reduce hydraulic losses in the afterburner on without afterburning mode when high reliability of the device is applicable to the field of aircraft engine industry and in particular, front-line devices afterburner combustion chambers.

Known afterburning chamber with front-line device with a radial stabilizers flame, that reduce the aerodynamic resistance to gas flow on without afterburning mode (see U.S. patent 4527390, CL IPC 7 F 02 To 3/06, publ. 09.07.1985).

In the known device the radial stabilizers consist of two flat plates, angled 90oto each other. They are connected to the articulated lever system with a drive, can be rotated about an axis and to reduce the 90oto the minimum value, while remaining in the gas stream and reducing, thus, only partially aerodynamic resistance (hydraulic losses) gas flow on without afterburning mode.

The closest in technical essence to the present invention is the device described in the patent of Russia 2018702, CL IPC 7 F 02 K 3/10, publ. 30.08.1994. Afterburner chamber air-jet engine contains front-line device with a radial stabilizers, flame, spaced evenly around the circumference can be rotated along the longitudinal axis of the camera relative to one of the ends of the stabilizer and connected with the actuator to move them.

The objective of the invention is the reduction of hydraulic losses in the afterburner on without afterburning mode when high reliability of the device rotation stabilizers along the longitudinal axis of the engine.

This technical result is achieved by the fact that the afterburning chamber air-jet engine includes an outer wall with split housings and with a heat shield, fuel manifold and front-line device with a radial stabilizers, flame, evenly spaced around the circumference of the gas flow duct with rotation along the axis of the camera by means of the drive mechanism made in the form of the of bilization supplied with brackets, moreover, the outer wall brackets pivotally connected with the outer ends of the stabilizers, and the arms of the middle part of stabilizers pivotally connected with adjustable thrust. The second end of the traction connected with duplechin lever connected with the rod of the hydraulic cylinder. Axis duplicera lever is made with a bore cylindrical necks, bearing on the outer side of the side brackets. Cervical involve in lehlohonolo landing with holes made in split housings of the exterior wall.

The invention is illustrated by drawings.

In Fig. 1 shows a longitudinal section of the afterburner jet-propulsion engine.

In Fig.2 shows the element "A" in Fig.1 in enlarged scale and rotated position, explaining the design of the double-arm lever of the front of the device and its connection with adjustable thrust, with split housings and with the piston rod of the hydraulic cylinder (view along the longitudinal axis).

In Fig.3 presents a cross-section b-b In Fig.2 in an enlarged scale, illustrating the construction of the main lever of the front of the device and its connection with adjustable thrust, with split housings cover and with the piston rod of the hydraulic cylinder.

In Fig.4 presents a view of B in Fig.1.

Afterburner chamber air-jet engine works as follows.

When the engine is in the afterburning mode 20 is connected with the drain line. The piston 18 is moved to the rightmost position (along the longitudinal axis of the engine). The rod 14 is moved to the right and through the side bracket 16 for mounting the neck 15 turns duplici lever 13 relative to the holes 17 in the plug housing 2, moves its inner end in the left extreme position, and adjustable rod 12 sets through the bracket 10, the stabilizer flame 6 in a vertical position relative to the camera axis, providing, thereby, creating zones of circulation, stabilizes the flame front.

When working on nonafterburning regimes in the right cavity 20 of the piston 18 is supplied to the working pressure and the left cavity 19 when this is connected with the drain line. The piston 18 is moved to the extreme left position (relative to the longitudinal axis of the engine). The rod 14 is moved in the left extreme position and through the side bracket 16 for mounting the neck 15 turns duplici lever 13 relative to the holes 17 in the plug housing 2 of the outer wall 1, moves the inner end duplicera lever 13 in the extreme right position. Adjustable rod 12 sets through the bracket 10, the stabilizer flame 3 in a horizontal position relative to the longitudinal axis of the chamber in the direction of movement on the part to remove the radial stabilizers of the gas flow, turning and placing them along the longitudinal axis of the engine at the inner wall of the front of the device, while ensuring minimal hydraulic losses of the gas flow on without afterburning mode, without engine power at the turn of the stabilizers and not worsening, thus, the specific parameters of the engine as a whole.

In addition, this embodiment of the front of the device allows you to seal the joints between the wall and the casing and to rotate the lever about its axis outside the hot gas almost in atmospheric conditions, eliminating a possible coking related nodes and increasing, thereby, the reliability of the device as a whole.

As shown by tests made by experienced full-sized sample afterburners, this embodiment of the front device with a retractable stabilizers and their location along the gas flow near the wall screen on nonafterburning modes reduces hydraulic losses in the afterburner 2.5. ..3%, which leads to an increase in thrust of 1.5...2% at high reliability steering stabilizers.

Claims

Afterburner chamber air-breathing engine, aderasa radial stabilizers, flame, evenly spaced around the circumference of the gas flow duct with rotation along the axis of the camera by means of the drive mechanism, made in the form of a hydraulic cylinder pivotally attached to the rear flange of the outer wall, while the outer wall and middle parts of the stabilizers supplied with brackets, and the brackets of the outer wall pivotally connected with the outer ends of the stabilizers, and the arms of the middle part of stabilizers pivotally connected with adjustable thrust, the other end of which is connected with two shoulders lever connected with the rod of the hydraulic cylinder, and the axis of the two shoulders of the lever is made with a bore cylindrical necks, bearing on the outer side of the side brackets and paired on lehlohonolo landing with holes made in split housings of the exterior wall.

 

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