JPH08135505A - Noise absorption equipment of jet propulsion mechanism for supersonic aircraft - Google Patents

Abstract

PURPOSE: To maintain a noise absorption function of noise absorption equipment at high temperature so as to reduce the volume of jet noise by providing a noise absorption material made of perforated plate and honeycomb positioned between a nozzle plate and a liner, and cooling the noise absorption equipment by cool air injected into the honeycomb through pores of the perforated plate along the nozzle plate. CONSTITUTION: This equipment comprises a nozzle plate 5, a liner 1, a perforated plate 4, a honeycomb 2 or the like. A noise absorption material is made of the honeycomb 2 and the perforated plate 4. On one surface of the honeycomb 2 positioned between the nozzle plate 5 and the liner 1, the perforated plate 4 is attached. On the other surface, a spacing side of the liner 1 is attached. A plurality of holes 11 are provided on the perforated plate 4 for introducing cool air injected from pores 10 of the perforated plate 4 into the honeycomb 2 and running against the spacing portion of the liner 1 into a fuel path through the holes 11. Thermal breakage caused by increasing temperature is prevented and a noise absorption function can be maintained.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a sound absorbing device for a jet propulsion engine for supersonic aircraft.

[0002]

2. Description of the Related Art FIG. 7 is a longitudinal sectional view of a turbofan engine 100 as a typical example of a jet propulsion engine for a supersonic aircraft. This propulsion organization, from the front, fan 1
01, compressor 102, combustor 103, high pressure turbine 10
4. Combustion gas generated from the gas generator section (the above-mentioned parts denoted by reference numerals 101 to 106) is composed of a low-pressure turbine 105, an afterburner 106, and an exhaust nozzle 107, flows in the direction of arrow 6, and passes through the exhaust nozzle 107 to the atmosphere. Spouts in.

FIG. 8 is a sectional view of the exhaust nozzle 107 shown in FIG.
It is a part expansion longitudinal sectional view. In the figure, 1 is a liner, 5 is a nozzle plate, 15 is an outer plate of an exhaust nozzle, and 6 is a high-temperature combustion gas flowing at high speed in the nozzle. The nozzle plate 5 and the outer plate 15 are structural strength members of the nozzle, which maintain the inner and outer shapes of the nozzle, and the liner 1 is provided with heat for preventing heat transfer and heat radiation to the structural strength member. It functions as a shielding plate. Reference numeral 7 is cooling air that flows between the liner 1 and the nozzle plate 5, and is for preventing the temperature rise of the liner 1.

[0004]

SUMMARY OF THE INVENTION In a jet propulsion engine for a subsonic aircraft, a fan mixer is mixed with exhaust gas by a flow mixer to lower the temperature of the exhaust gas, and noise is prevented by attaching a sound absorbing material thereto. However, the supersonic aircraft jet propulsion engine cannot use a large bypass ratio from the fan and cannot reduce the exhaust gas temperature, so it can be used under combustion gas close to 2000 ° C. The lack of sound absorbers does not allow the use of noise suppression techniques established in subsonic aircraft jet propulsion engines to prevent noise from exhaust jets. For this reason, the conventional supersonic aircraft jet propulsion engine has been used without a sound absorbing function.

[0005] The present invention solves the above deficiencies of the prior art,
It is an object of the present invention to provide a sound absorbing device applicable to a supersonic aircraft jet propulsion engine having a high exhaust gas temperature.

[0006]

SUMMARY OF THE INVENTION The present invention has been made to solve the above-mentioned problems, and comprises an exhaust nozzle having a nozzle plate and a liner provided with a gap on a side of a combustion gas passage thereof. The present invention relates to a supersonic aircraft jet propulsion engine to which cooling air is supplied, and to a sound absorbing device for a supersonic aircraft jet propulsion engine having the following features.

(1) Between the nozzle plate and the liner, the other surface of the honeycomb having a perforated plate attached to one surface thereof is provided so as to contact the surface of the liner on the gap side,
A large number of holes were provided in the liner to guide the cooling air flowing into the honeycomb through the holes in the perforated plate and colliding with the surface of the liner on the gap side to the surface of the liner on the side of the combustion gas passage.

(2) Between the nozzle plate and the liner, the other side of the truss core having a perforated plate attached to one surface is provided in contact with the surface of the liner on the gap side, and the hole of the perforated plate is provided. The liner is provided with a large number of holes for guiding the cooling air flowing into the truss core through the above and colliding with the gap side surface of the liner to the combustion gas passage side surface of the liner.

(3) Between the nozzle plate and the liner, the other side of the honeycomb having a perforated plate on one side is provided in contact with the gap side surface of the liner, and
The honeycomb was provided with a large number of holes for guiding the cooling air flowing into the honeycomb through the holes in the perforated plate and colliding with the gap side surface of the liner to the rear of the exhaust nozzle.

(4) Between the nozzle plate and the liner, the other side of the truss core having a perforated plate mounted on one side thereof is provided so as to abut against the surface of the liner on the gap side.

(5) Between the nozzle plate and the liner, a honeycomb or truss core having porous plates attached on both sides is arranged, and the holes or holes in one of the porous plates flow into the honeycomb or truss core and the other porous plate is introduced. The liner is provided with a large number of holes for guiding the cooling air ejected from the holes of the plate and colliding with the gap side surface of the liner to the combustion gas passage side surface of the liner.

In each of the above inventions, the sound absorbing material is formed by attaching a perforated plate to the honeycomb or the truss core, and the cooling air supplied along the nozzle plate is prevented in order to prevent thermal damage due to a rise in temperature of the sound absorbing material. It is introduced into the honeycomb or truss core through holes in the perforated plate and cooled to prevent breakage and maintain its function as a sound absorbing material.

The cooling air introduced from the perforated plate of the sound absorbing material and passed through the honeycomb or the truss core impinges on the liner by impingement cooling the liner, or is ejected from a hole provided in the liner to the combustion gas passage side of the liner. By letting the liner film cool,
The liner, which functions as a heat shield, is prevented from rising in temperature.

[0014]

1 is a diagram showing a sound absorbing device for a supersonic jet propulsion engine according to a first embodiment of the present invention, in which (a) is a longitudinal sectional view and (b) is a perspective view. is there. In the figure, 5 is a nozzle plate, 1 is a liner, 4 is a perforated plate,
2 is a honeycomb formed between the liner 1 and the perforated plate 4; 10 is a hole in the perforated plate 4; 11 is a hole inclined backward in the liner 1; 6 is a combustion gas; , 8
Is impingement air flowing into the honeycomb 2 through the hole 10 of the perforated plate 4 and colliding with the liner 1, and 9 is ejected from the honeycomb 2 through the hole 11 of the liner 1 and is exposed to the combustion gas of the liner 1. This is film air formed as a film of air on the surface of the film.

In the present embodiment, the sound absorbing material is a portion composed of the honeycomb 2 and the perforated plate 4, which is combined with the liner and the nozzle plate 5 to constitute a sound absorbing device, and the jet noise generated by the combustion gas 6. And reduce noise levels.

To cool the sound absorbing device, cooling air 7 flows between the nozzle plate 5 and the perforated plate 4 to cool the nozzle plate and impinge air 8 impinges on the liner 1 from the hole 10 in the perforated plate 4. Then, the film air 9 is blown out toward the combustion gas 6 through a hole 11 formed in the liner 1 to cool the liner 1 from inside and outside.

FIGS. 2A and 2B are views showing a sound absorbing device according to a second embodiment of the present invention, wherein FIG. 2A is a longitudinal sectional view and FIG. 2B is a perspective view. In the present embodiment, a tiger score 3 is used instead of the honeycomb 2 in the first embodiment, and reference numeral 14 denotes a hole of the tiger score 3. Other configurations are the same as in the first embodiment. The sound absorbing function and the cooling function are the same as in the first embodiment. Since this embodiment has a truss structure,
The deformation followability to thermal elongation is higher than that of the first embodiment.

FIG. 3 is a longitudinal sectional view of a sound absorbing device according to a third embodiment of the present invention. In the present embodiment, the holes 11 provided in the liner 1 in the first embodiment are omitted. Reference numeral 12 denotes an air passage hole provided in the honeycomb 2 along the liner 1 and communicating with the internal space of the honeycomb.
In this embodiment, there is no film air cooling on the side of the liner 1 exposed to the combustion gas 6, and the hole 1 provided in the honeycomb 2 is not provided.
The cooling air flows toward the rear of the nozzle along the honeycomb-side surface of the liner 1 via the line 2, and the forced convection and the impingement air 8 cool the liner 1 only from one side. Since the hole 11 of the liner 1 is not processed in this embodiment,
The feature is that the cost is low. Since the honeycomb 2 has the air passage holes 12, the sound absorbing effect is slightly lower than that of the first embodiment.

FIG. 4 is a longitudinal sectional view of a sound absorbing device according to a fourth embodiment of the present invention. In the present embodiment, the holes 11 provided in the liner 1 in the second embodiment are omitted. In the present embodiment, as in the third embodiment, cooling air flows along one surface of the liner 1, and this forced convection and
The liner 1 is cooled by the impingement air 8. The feature is that the processing cost required for the hole 11 of the liner can be reduced. The sound absorbing action is almost the same as in the second embodiment.

FIG. 5 is a longitudinal sectional view of a sound absorbing device according to a fifth embodiment of the present invention. In the present embodiment, a perforated plate 4 is also provided on the liner 1 side of the honeycomb 2, a gap is provided between the liner-side perforated plate 4 and the liner 1, and the impingement air 8 is transferred from the hole 13 of the liner-side perforated plate 4 to the liner 1. 1 and is blown out from the hole 11 of the liner 1 toward the combustion gas 6 to cool the liner 1 by film air 9.

In this embodiment, the honeycomb portion has an independent structure, so that the height of the honeycomb can be arbitrarily set, whereby the sound absorbing effect can be further improved and the high cooling effect can be maintained. Further, since the honeycomb and the liner are separated from each other, the deformability following the thermal expansion is higher than that of the first embodiment. The cooling effect of the liner is the same as in the first embodiment.

FIG. 6 is a longitudinal sectional view of a sound absorbing device according to a sixth embodiment of the present invention. In the present invention, a perforated plate 4 is also provided on the liner 1 side of the truss core 3 to make the truss core portion independent of the liner, and the impingement air 8 is moved from the truss core to the hole 13.
Through the hole 11 of the liner, and blows out the film air 9 through the hole 11 of the liner. The operation and effect of this embodiment are almost the same as those of the fifth embodiment.

[0023]

The sound absorbing device for a supersonic jet propulsion engine according to the present invention is constructed by providing a sound absorbing material comprising a perforated plate and a honeycomb or a perforated plate and a truss core between a nozzle plate and a liner. In order to prevent heat damage due to temperature rise of the material, cooling air supplied along the nozzle plate is introduced into the honeycomb or truss core through holes in the perforated plate and cooled, preventing the damage, and as a sound absorbing material under high temperature Since the function is maintained, noise due to the jet can be reduced.

The cooling air introduced from the perforated plate of the sound absorbing material and passed through the honeycomb or the truss core impinges on the liner by impinging on the liner, or is ejected from a hole provided in the liner to the combustion gas passage side of the liner. As a result, the liner is film-cooled, so that the liner can function as a heat shield under high temperatures, as before.

[Brief description of drawings]

FIG. 1 is a diagram of a sound absorbing device according to a first embodiment of the present invention, in which (a) is a longitudinal sectional view and (b) is a perspective view.

FIGS. 2A and 2B are diagrams of a sound absorbing device according to a second embodiment of the present invention, wherein FIG. 2A is a longitudinal sectional view and FIG.

FIG. 3 is a vertical sectional view of a sound absorbing device according to a third embodiment of the invention.

FIG. 4 is a longitudinal sectional view of a sound absorbing device according to a fourth embodiment of the present invention.

FIG. 5 is a longitudinal sectional view of a sound absorbing device according to a fifth embodiment of the present invention.

FIG. 6 is a vertical sectional view of a sound absorbing device according to a sixth embodiment of the present invention.

FIG. 7 is a longitudinal cross-sectional view of a typical supersonic aircraft jet propulsion engine.

8 is a vertical sectional view of an exhaust nozzle of the propulsion engine (an enlarged view of a portion A in FIG. 7).

[Explanation of symbols]

 1 Liner 2 Honeycomb 3 Truss Core 4 Perforated Plate 5 Nozzle Plate 6 Combustion Gas 7 Cooling Air 8 Impinge Air 9 Film Air 10 Perforated Plate Hole 11 Liner Hole (Inclined) 12 Honeycomb Hole 13 Liner Side Perforated Plate Hole 14 Truscore Hole 15 Exhaust nozzle outer plate

Claims (5)

[Claims] 1. A supersonic aircraft jet propulsion engine, comprising: a nozzle plate and an exhaust nozzle having a liner provided on a combustion gas passage side thereof with a gap therebetween, and cooling air being supplied to the gap. Between the nozzle plate and the liner, the other side of the honeycomb having the perforated plate attached on one side is provided in contact with the gap side surface of the liner, and flows into the honeycomb through the hole of the perforated plate. The liner is provided with a number of holes for guiding the cooling air colliding with the surface of the liner on the gap side to the surface of the liner on the side of the combustion gas passage, and the sound absorption of the jet propulsion engine for a supersonic aircraft is provided. apparatus. 2. A supersonic aircraft jet propulsion engine, comprising: a nozzle plate and an exhaust nozzle having a liner provided on a combustion gas passage side thereof with a gap provided therebetween, and cooling air being supplied to the gap. Between the nozzle plate and the liner, the other side of the truss core having a perforated plate attached to one side thereof is provided in contact with the gap side surface of the liner, and flows into the truss core through a hole in the perforated plate. The liner is provided with a number of holes for guiding the cooling air colliding with the surface of the liner on the gap side to the surface of the liner on the side of the combustion gas passage, and the sound absorption of the jet propulsion engine for a supersonic aircraft is provided. apparatus. 3. A supersonic aircraft jet propulsion engine, comprising: a nozzle plate and an exhaust nozzle having a liner provided on a combustion gas passage side thereof with a gap provided therebetween, wherein cooling air is supplied to the gap. Between the nozzle plate and the liner, the other side of the honeycomb having the perforated plate attached on one side is provided in contact with the gap side surface of the liner, and flows into the honeycomb through the hole of the perforated plate. A sound absorbing device for a jet propulsion engine for a supersonic aircraft, wherein a number of holes are provided in the honeycomb for guiding the cooling air colliding with the surface of the liner on the gap side to the rear of an exhaust nozzle. 4. A supersonic aircraft jet propulsion engine, comprising: a nozzle plate and an exhaust nozzle having a liner provided on the combustion gas passage side thereof with a gap provided therebetween, wherein cooling air is supplied to the gap. A jet propulsion for a supersonic aircraft, wherein the other side of the truss core having a perforated plate mounted on one surface thereof is provided between the nozzle plate and the liner so as to abut against the surface of the liner on the gap side. Engine sound absorber. 5. A supersonic aircraft jet propulsion engine, comprising: a nozzle plate and an exhaust nozzle having a liner provided on a combustion gas passage side thereof with a gap provided therebetween, and cooling air being supplied to the gap. A honeycomb or truss core having a perforated plate attached to both sides is disposed between the nozzle plate and the liner, and flows into the honeycomb or truss core from a hole in one of the perforated plates and flows out from a hole in the other perforated plate. A plurality of holes in the liner for guiding the cooling air colliding with a surface of the liner on a gap side of the liner to a surface of the liner on a combustion gas passage side. apparatus.