JPH1068355A - Air turbo-ramjet engine - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a high propulsion efficiency in a wide speed range from a speed during take-off (M0) to a supersonic speed (M6), to perform high- efficient mixture of a small quantity of fuel and air, to shorten an overall length, to make light in weight, to facilitate proper cooling, and to have high energy efficiency. SOLUTION: An air turbo ram jet engine comprises a rotation support member 13 to rotate and support a turbine 2 and a fan 4; a hollow annular toroidal type ram combustor 14 communicated with the rear of the rotation support member and having a mixer 3 to mix together compressed air and fuel gas; and a plug nozzle 16 coupled to the rear of the ram burner. The ram burner consists of a truncated conical type burner inner cylinder 15a having a rear being spread and a burner outer cylinder 15b. The front edge of the burner inner cylinder is coupled to a rotary support member, and the rear edge of the burner inner cylinder is coupled to the inner plug of the plug nozzle. Further, a heat-exchanger 19 to vaporize liquid fuel is provided and at least a part of a cooling pipe through which liquid fuel of the heat-exchanger flows is disposed along the surface of an internal plug 17.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

[0001] The present invention relates to an air turbo ramjet engine.

[0002]

2. Description of the Related Art An air turbo ramjet engine (hereinafter, referred to as an ATR engine) is a combined cycle engine of a turbojet and a ramjet, and can be roughly classified into a gas generator type and an expander type.

FIG. 5 shows an expander type ATR engine. In addition to a turbine 2, a mixer 3, a fan 4, a ram combustor 5, an exhaust nozzle 6, etc., a heat exchanger 7 is used instead of a gas generator. The heat exchanger 7 evaporates and expands liquid fuel (for example, liquid hydrogen) to generate a high-temperature and high-pressure fuel gas, and drives the turbine 2 with the generated fuel gas. Compressed gas is introduced, the introduced air and fuel gas are mixed by the mixer 3, the mixed gas is burned by the combustor 5, and the combustion exhaust gas is expanded by the exhaust nozzle 6 and jetted backward to generate thrust. It has become. Further, in this figure, the turbine 2 is directly connected to the outer peripheral portion of the fan 4, so that the overall length is shortened and the transmission efficiency is increased.

The above-described conventional ATR engine generates a high thrust even at a low speed of Mach 1 (M1) or less, can take off on its own, and has a Mach 6 (M6) or higher similarly to a ramjet. There is a feature that can also supersonic flight.

[0005]

As an exhaust nozzle of an ATR engine, a convergent divergent nozzle 6 (hereinafter referred to as a CD nozzle) illustrated in FIG. 5 is used. However, in the case of a CD nozzle, the variable width of the expansion ratio is limited to about four times, and the CD flap can handle only M0 to M2. In contrast, the ATR engine uses M0
The required variable width of the exhaust nozzle reaches about 25 times as applied to flight in the range of ~ M6. For this reason, the conventional CD nozzle has a problem that the propulsion efficiency at M2 or higher is greatly reduced.

Further, the conventional CD nozzle requires a divergent flap angle variable mechanism and an actuator in order to obtain a nozzle expansion ratio (exit area / throat area) corresponding to the flight Mach number. There was a problem that the weight increased.

As shown in FIG. 5, in the conventional ATR engine, a ram combustor 5 is disposed in a cylindrical combustion chamber, and a lob mixer 3 is used to promote mixing of air and fuel gas. However, since the volume of the fuel gas (for example, hydrogen gas) is smaller than that of air, the mixing efficiency is low in a cylindrical combustion chamber (ram combustor) having a large cross-sectional area. There was a problem to do.

The present invention has been made to solve the various problems described above. That is, the first of the present invention
The purpose of this is to take off (M
An object of the present invention is to provide an air turbo ramjet engine having high propulsion efficiency in a wide speed range from 0) to supersonic speed (M6). A second object is to provide an air turbo ramjet engine that can efficiently mix a small amount of fuel and air. It is a third object of the present invention to provide an air turbo ram jet engine which has a short overall length, is lightweight, can appropriately cool each part, and has high energy efficiency.

[0009]

According to the present invention, a hollow annular member having a rotary support member for rotatably supporting a turbine and a fan, and a mixer connected behind the rotary support member for mixing compressed air and fuel gas. An annular ram combustor, and a plug nozzle connected to the rear of the ram combustor;
An air turbo ramjet engine is provided. According to a preferred embodiment of the present invention, the plug nozzle includes an inner plug having a conical surface continuously formed coaxially behind the spherical portion, and an outer duct surrounding the spherical portion of the internal plug at an interval. Consisting of
Jet is injected from between the inner plug and the outer duct.

According to the configuration of the present invention, since a plug nozzle is provided, a wide flight Mach number can be handled without an expansion ratio adjusting mechanism. That is, since the plug nozzle automatically balances the outside air and the exhaust flow according to the static pressure difference, high efficiency can be achieved at a wide Mach number of M0 to M6, and a flap variable mechanism unlike a CD nozzle is not required. The weight of the nozzle can be reduced. In addition, an annular ram combustor having a mixer for mixing compressed air and fuel gas is provided.In an annular hollow annular space, the penetration force of hydrogen into the air is relatively increased, and a small amount of fuel is used. It can be efficiently mixed with air.

The annular type ram combustor comprises a frusto-conical combustor inner cylinder and a combustor outer cylinder whose rear diameter is enlarged, and a front edge of the combustor inner cylinder is connected to a rotation support member. The rear edge of the combustor inner cylinder is connected to the internal plug of the plug nozzle. With this configuration, the forward jet reaction force acting on the plug nozzle can be transmitted to the rotary support member via the combustor inner cylinder, and acts on the connecting member between the inner plug and the outer duct exposed to the high-temperature gas. Force can be reduced, the overall length can be shortened, and the size and weight can be reduced.

[0012] Further, a heat exchanger for evaporating the liquid fuel is provided, and at least a part of a cooling pipe through which the liquid fuel of the heat exchanger passes is disposed along a surface of the internal plug.
With this configuration, it is possible to simultaneously generate the hydrogen gas for driving the turbine and cool the internal plug exposed to the high-temperature gas, and to appropriately cool each part and obtain high energy efficiency.

[0013]

Preferred embodiments of the present invention will be described below with reference to the drawings. In each of the drawings, common portions are denoted by the same reference numerals, and redundant description will be omitted. FIG. 1 is a principle diagram of a plug nozzle. The throat area St in the plug nozzle 11 is equal to the outer duct 1
2 is the side area of the truncated cone having the perpendicular as the generatrix dropped from the end of the plug 11p to the surface of the plug 11p. I do. That is, the combustion exhaust gas expands and contracts freely according to the balance with the atmospheric pressure and jets out, and the flow area of the combustion exhaust gas on the virtual plane is calculated as the exit area Se. For example, at a low speed of about Mach 1,
The combustion exhaust gas is spouted out along the surface of the plug 11p, and the area of the edge of the diameter Ds in the virtual plane is the exit area Se.
On the other hand, when a supersonic velocity such as Mach 5 is reached, the flue gas separates from the surface of the plug 11p, expands from the end of the outer duct 12, and jets out. . Therefore, since the aperture ratio (exit area Se / throat area St) changes freely to match the flight speed, there is no need to provide a variable mechanism for actively changing the aperture ratio, and the aperture ratio is adapted to a wide range of aperture ratio. .

FIG. 2 shows an example of test results of the plug nozzle described above, which was published in the United States in 1954 ("EFFECT OF PLUG DESIGN ON PERFORMANCE CH").
ARACTERISTICS OF CONVERGENT-PLUG EXHAUST NOZZLES ",
NATIONAL ADVISTORY COMMITTEE FOR AERONAUTICS, Oct
ober 25, 1954). In this figure, the horizontal axis is the pressure ratio (Nozzle pressure ratio) at the exhaust nozzle, and the vertical axis is the thrust coefficient (Thrust coefficient). In the figure, Δ indicates reference data of a conventional CD nozzle, and ○ and □ indicate data of a plug nozzle. From this figure, it can be seen that the above-described plug nozzle can obtain higher efficiency in a wide range of pressure ratios than the CD nozzle.

The above-described plug nozzle has the advantage of having high efficiency over a wide range of flight speeds, but has a large jet reaction force acting on the plug and receives the reaction force (a connecting member between the inner plug and the outer duct). ) Is exposed to a high-temperature gas, so that the strength of the member becomes extremely small. Further, the plug itself located inside the plug nozzle is also exposed to the high-temperature gas and has a short life. It was difficult.

FIG. 3 is an overall configuration diagram of the air turbo ramjet engine of the present invention, and FIG. 4 is a schematic diagram of FIG. 3 and 4, an air turbo ramjet engine 10 according to the present invention includes a rotating support member 13 for rotatingly supporting a turbine 2 and a fan 4, and a compressed air and a fuel gas connected to the rear of the rotating support member 13. A hollow annular annular ram combustor 14 having a mixer 3 and a plug nozzle 16 connected to the rear of the ram combustor 14;
It has.

The plug nozzle 16 includes an inner plug 17 having a conical surface 17b formed coaxially and continuously behind the spherical portion 17a, and an outer duct 18 surrounding the spherical portion 17a of the internal plug 17 at a distance. The jet is jetted from between the inner plug 17 and the outer duct 18. With this configuration, since the plug nozzle 16 is provided, it is possible to cope with a wide flight Mach number without an expansion ratio adjusting mechanism.
That is, since the plug nozzle 16 automatically balances the outside air and the exhaust flow according to the static pressure difference as described above, the plug nozzle 16 can achieve high efficiency at a wide Mach number of M0 to M6, and has a flap variable mechanism like a CD nozzle. Since no nozzle is required, the weight of the nozzle can be reduced.

As shown in FIGS. 3 and 4, the air turbo ramjet engine 10 of the present invention further includes a heat exchanger 19 for evaporating liquid fuel (for example, liquid hydrogen). The heat exchanger 19 includes an evaporating portion 19 a provided along the surface of the internal plug 17, and an expansion portion 19 b located between the internal plug 17 and the outer duct 18. The liquid fuel (for example, liquid hydrogen) flowing through the cooling pipe of the evaporator 19a evaporates while flowing along the surface of the internal plug 17, and cools the internal plug 17 by the heat of evaporation. In the expansion section 19b, the evaporated fuel gas is further heated and expanded into a high-temperature and high-pressure fuel gas by heat exchange with the high-temperature combustion gas supplied from the ram combustor 14, and supplied to the turbine 2. ing.
With this configuration, the generation of the turbine driving gas and the cooling of the internal plug 17 exposed to the high-temperature gas can be performed at the same time, so that each part can be appropriately cooled and high energy efficiency can be obtained.

The annular type ram combustor 14 has a frusto-conical combustor inner cylinder 15a and a combustor outer cylinder 15b with a rearwardly enlarged diameter.
Consists of The front edge of the combustor inner cylinder 15 a is connected to the rotation support member 13, and the rear edge of the combustor inner cylinder 15 a is connected to the internal plug 17 of the plug nozzle 16. With this configuration, the forward jet reaction force acting on the plug nozzle 16 is applied to the rotation support member 1 via the combustor inner cylinder 15a.
3, the force acting on the connecting member between the inner plug 17 and the outer duct 18 exposed to the high-temperature gas can be reduced, and the overall length can be reduced and the size and weight can be reduced.

It should be noted that the present invention is not limited to the above-described embodiment, and it goes without saying that various changes can be made without departing from the spirit of the present invention.

[0021]

As described above, the air turbo ramjet engine of the present invention has no complicated mechanism,
It has high propulsion efficiency in a wide speed range from takeoff (M0) to supersonic speed (M6), can efficiently mix a small amount of fuel and air, has a short overall length, is lightweight, and has various components. It can cool properly and has high energy efficiency,
And so on.

[Brief description of the drawings]

FIG. 1 is a principle diagram of a plug nozzle.

FIG. 2 is an example of a test result of a plug nozzle.

FIG. 3 is an overall configuration diagram of an air turbo ramjet engine of the present invention.

FIG. 4 is a schematic diagram of FIG.

FIG. 5 is a schematic view of a conventional air turbo ramjet engine.

[Explanation of symbols]

 2 Turbine 3 Mixer (Rob Mixer) 4 Fan (Compressor) 5 Combustor 6 Exhaust Nozzle (CD Nozzle) 7 Heat Exchanger 10 Air Turbo Ram Jet Engine 11 Plug Nozzle 11p Plug 12 Outer Duct 13 Rotation Support Member 14 Annular Ram Combustion Device 15a Combustor inner cylinder 15b Combustor outer cylinder 16 Plug nozzle 17 Inner plug 18 Outer duct 19 Heat exchanger 19a Evaporator 19b Expansion unit

Claims (4)

[Claims] 1. A hollow annular annular type ram combustor having a rotary support member rotatably supporting a turbine and a fan, a mixer connected behind the rotary support member and mixing compressed air and fuel gas, and the ram. An air turbo ram jet engine, comprising: a plug nozzle connected to the rear of the combustor. 2. The plug nozzle, comprising: an inner plug having a conical surface formed continuously coaxially behind the spherical portion; an outer duct surrounding the spherical portion of the internal plug at an interval;
The air turbo ram jet engine according to claim 1, wherein the jet is jetted from between the inner plug and the outer duct. 3. The annular type ram combustor includes a frusto-conical combustor inner cylinder and a combustor outer cylinder whose rear diameter is increased.
The air turbo ram jet engine according to claim 2, wherein a leading edge of the combustor inner cylinder is connected to the rotation support member, and a trailing edge of the combustor inner cylinder is connected to the internal plug of the plug nozzle. . 4. A heat exchanger for evaporating the liquid fuel, wherein at least a part of a cooling pipe for passing the liquid fuel of the heat exchanger is disposed along a surface of the internal plug.
The air turbo ram jet engine according to claim 2, wherein: