JPH11107857A - Air turbo ram engine - Google Patents

Abstract

PROBLEM TO BE SOLVED: To cool a tip turbine effectively and also to improve cycle performance by inducing hydrogen gas bypassed through a heat exchanger from a cold hydrogen supply source into a tip turbine, and installing an inlet passage to cool this tip turbine. SOLUTION: At the time of a slow flight of an air turbo ram jet engine, a driving gas Hd heated and generated by way of a heat exchanging part is taken into a peripheral side gas passage 17b via a receiving part 21, driving a tip bucket 24. Simultaneously, a cooling gas Hc bypassed with the heat exchanging part is made to flow into a cooling hole 28 of the tip bucket 24 by way of a through hole 22 of the receiving part 21 and an inner circumferential side gas passage 17a, whereby this tip bucket 24 is film-cooled. In addition, a part of the cooling gas Hc induced into the inner circumferential gas passage 17a is emitted to the inner circumferential side gas passage 17a by way of a bucket side gas passage 25 of the tip bucket 24. The cooling gas Hc passed through a bucket side gas passage 24 is reemitted to the inner circumferential side gas passage 17a by way of a bucket side gas passage 27. With this constitution, the tip bucket 24 and the tip stator blade 26 are cooled.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an air turbo ram engine which obtains propulsion by burning fuel (liquid hydrogen) using air taken in flight as an oxidant,
In particular, it relates to an expander cycle type air turbo ram engine.

[0002]

2. Description of the Related Art Conventionally, while in flight, air in the atmosphere is sucked, and liquid hydrogen, which is a fuel, is used as an oxidant to burn the air. Air turbob engine (Air Turb
o Ram Engine: An ATR engine is known.

Since the ATR engine takes in the oxidant from the atmosphere, it does not need to fly with liquid oxygen as in a conventional rocket, so that the weight reduced by this is diverted to the structural weight of the fuselage. This has the advantage that safety and reliability comparable to aircraft can be achieved.

FIG. 4 is a diagram schematically showing an example of the structure of an ATR engine employing an expander cycle utilizing aerodynamic heating as regenerative energy while utilizing the characteristics of liquid hydrogen as a refrigerant.

In this ATR engine, a tip turbine 2 is provided at the tip of a moving blade 1. During low-speed flight, low-temperature hydrogen from a low-temperature hydrogen supply source (not shown) is supplied to a flow path 3 in which the tip turbine 2 is disposed. Is supplied to the heat exchanging section 4 and the heated and generated hydrogen gas is introduced as a driving gas Hd to drive the bucket 1.

[0006] The driving gas Hd that drives the rotor blade 1
Is mixed with the intake air A by a mixer (not shown) arranged downstream of the flow path 3, and the mixed gas is burned in the combustion chamber 5 so that a high-temperature and high-speed gas flow is injected backward. That gives you the propulsion.

[0007] In the ATR engine having such a configuration, by adopting a tip turbine structure in a turbomachine portion for sucking air at a low speed flight, the safety and reliability described above are ensured, and the conventional ATR engine is used for a conventional aircraft jet engine. It is a compact and lightweight engine that cannot be seen.

[0008]

By the way, in a normal jet engine, the turbine blades are cooled by using the intake air to thereby improve the heat resistance against an increase in the inlet temperature. In the engine, when the intake air A is introduced into the flow path 3, it reacts with the driving gas Hd and burns. Therefore, the chip turbine 2 is used in an uncooled state.

For this reason, in order to further improve the cycle performance by further increasing the inlet temperature, there is a certain limit in relation to the heat resistance of the chip turbine 2. As a method of improving the heat resistance of the chip turbine 2, it is conceivable to change the material of the chip turbine 2 to a high heat-resistant material, but such a material has not yet been realized at the development stage.

The present invention has been made in view of the above circumstances, and has as its object to provide an ATR engine capable of improving the cycle performance by effectively cooling a chip turbine.

[0011]

In order to solve the above-mentioned problems, the present invention employs the following configuration in an ATR engine. (a) An introduction path for cooling the chip turbine by introducing hydrogen gas bypassing the heat exchange section from the low-temperature hydrogen supply source as a cooling gas into the inside of the chip turbine was provided. (b) The chip moving blade is provided with a cooling hole for cooling the chip moving blade by discharging the cooling gas from the introduction path toward the flow path of the driving gas. (c) The moving blade side gas passage for passing the cooling gas passing through the introduction passage toward the tip stationary blade provided on the downstream side of the moving blade is provided in the moving blade. (d) The tip stationary blade is provided with a stationary blade side gas passage for passing the cooling gas passing through the moving blade side gas passage toward the tip stationary blade provided on the downstream side of the tip stationary blade.

[0012]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS One embodiment of an ATR engine according to the present invention will be described below with reference to FIGS.

FIG. 1 is a schematic diagram showing the structure of an ATR engine. The ATR engine is provided with an introduction path 10 that bypasses the heat exchange section 4 for a part of low-temperature hydrogen supplied from a low-temperature hydrogen supply source (not shown) and introduces the cooling gas Hc into the chip turbine 2.

FIG. 2 is a sectional view of the ATR engine. This ATR engine includes a cylindrical shroud 11 and a cylindrical center body 13 coaxially fixed by a strut 12 inside the shroud 11, and a main shaft 14 includes a bearing 15 inside the center body 13. 16
Are supported rotatably.

In the shroud 11, a space formed between the shroud 11 and the center body 13 is provided with a gas passage 17 and an intake air passage 1.
8 and a support member 20 that supports two sets of stationary blades 19 extending toward the center body 13 is fixed.

A receiving portion 21 is connected to the tip of the shroud 11 for supplying low-temperature hydrogen from a low-temperature hydrogen supply source to the heat exchange portion 4 and introducing the drive gas Hd generated by heating into the outer gas passage 17b. I have. The receiving portion 21 has a cylindrical shape with a bottom having a flange on the opening end side, and a through hole 22 penetrating in the diametrical direction is formed in the bottom portion.

The introduction passage 10 is connected to the through-hole 22 so that low-temperature hydrogen bypassing the heat exchange section 4 is introduced as cooling gas Hc into the inner peripheral gas passage 17a.

At the tip of the main shaft 14, two sets of moving blades 23 extending radially from the peripheral surface are arranged at intervals in the axial direction of the main shaft 14 so as to be arranged on the upstream side of each of the stationary blades 19. Is provided. The moving blade 23 and the stationary blade 19 constitute a compressor.

FIG. 3 is a sectional view of an essential part of the ATR engine in FIG. The moving blade 2 arranged on the upstream side among the moving blades 23
A tip blade 24 having a comb-shaped cross section is provided at the tip of 3a. The cooling gas Hc introduced from the introduction path 10 into the inner peripheral gas passage 17a flows into the tip moving blade 24 from the front of the tip moving blade 24, and is discharged from the rear into the inner peripheral gas passage 17a. A moving blade side gas passage 25 is formed.

A tip stationary blade 26 radially inwardly extending is provided on the inner peripheral surface of the shroud 11 where the tip end surface of the tip rotor blade 24 faces. This tip stationary blade 26
Is formed with a vane-side gas passage 27 that allows the cooling gas Hc discharged from the tip blade 24 to flow in from the front of the tip vane 26 and discharges the cooling gas Hc from the rear to the inner peripheral gas flow path 17a.

Further, the cooling gas Hc introduced into the inner peripheral side gas flow path 17a is supplied to the tip moving blades 24.
Of the tip rotor blade 2 and discharged from the upper end of the tip rotor blade 24 toward the outer peripheral gas passage 17b.
A cooling hole 28 for cooling the film 4 is formed.

As described above, the chip turbine 2 is configured by the chip moving blades 24 and the chip stationary blades 26 that supply low-temperature hydrogen to the heat exchange section 4 and are rotationally driven by the heated and generated driving gas Hd. Then, the driving gas Hd after the tip blade 24 is rotationally driven is mixed with the intake air A by the mixer 29 and burned to be used as fuel for generating thrust.

Further, a cooling mechanism provided in the chip turbine 2 supplies low-temperature hydrogen as a cooling gas Hc from the through hole 22 to the inner peripheral side driving gas flow path 17a,
And blade-side gas passage 2 formed in tip stationary blade 26
5. The chip turbine 2 is cooled by flowing through the stationary blade side gas passage 27 and the cooling holes 28.

Next, the operation of the ATR engine having the above configuration during low-speed flight will be described. First, the hydrogen gas heated and generated by passing the heat from the low-temperature hydrogen supply source through the heat exchange unit 4 is used as the driving gas Hd in the receiving unit 21.
Is introduced into the gas flow path 17b on the outer side where the upper end of the tip blade 24 is disposed, and drives the tip blade 24.

At the same time, it flows into the introduction path 10 and
Gas that bypasses the gas receiving section 21 as a cooling gas Hc.
Flows through the through hole 22 formed at the bottom of the tip rotor blade 2.
4 is introduced into the inner peripheral gas passage 17a in which the lower end is disposed.

The cooling gas Hc introduced into the inner peripheral gas passage 17a flows into a cooling hole 28 formed in the tip moving blade 24 arranged at the most upstream side, and from the upper end of the tip moving blade 24 to the outer peripheral side. The tip blade 2 is discharged toward the gas flow path 17b and
4 is film cooled.

A part of the cooling gas Hc introduced into the inner peripheral gas passage 17a flows through the moving blade side gas passage 25 formed in the tip moving blade 24, and then flows into the inner peripheral gas passage 17a.
Will be released.

The cooling gas H that has passed through the blade-side gas passage 25
c is a blade-side gas passage 27 formed in the tip stationary blade 26.
And then discharged again to the inner peripheral gas passage 17a.

As described above, the cooling gas Hc flows upstream through the inner peripheral gas passage 17a while sequentially flowing through the moving blade side gas passage 25 and the stationary blade side gas passage 27 provided in the tip moving blade 24 and the tip stationary blade 26. By flowing from the side to the downstream side, the tip moving blades 24 and the tip stationary blades 26 are cooled. Further, in the process, a part of the cooling gas Hc flows into the cooling hole 28 and is discharged to the outer peripheral gas passage 17b, so that the tip blade 24 is film-cooled.

According to the ATR engine configured as described above, the tip turbine 2 is cooled by using a part of the low-temperature hydrogen which is the fuel, thereby improving the heat resistance of the tip turbine 2 and further increasing the inlet temperature. Since the temperature can be increased, the cycle performance can be improved.

The rotation of the rotor blades 23 causes the cooling gas H
Since c is ejected downstream, mixing of the drive gas Hd and the intake air A downstream is promoted. As a result, the combustion efficiency can be improved, the combustion distance of the combustor 29 can be shortened, and the size of the ATR engine can be further reduced.

Further, in the expander type ATR engine, a heat exchanger for regenerating and heating low-temperature hydrogen is indispensable. In the ATR engine of this embodiment, a part of the low-temperature hydrogen is used as a cooling gas Hc as a chip turbine. 2 is used for cooling, and a part of the heat exchange function can be replaced by heat exchange with the chip turbine 2 performed at that time.

In the ATR engine of this embodiment,
By sealing a sealing gas G such as a nitrogen gas or a helium gas from the upstream side and the downstream side of the gas flow path 17,
Leakage of the driving gas Hd and the cooling gas Hc from the gas flow path 17 is prevented, and mixed combustion with the intake air A is avoided.

[0034]

As is clear from the above description, according to the present invention, the following effects can be obtained. (a) Since the chip turbine can be cooled very effectively using a part of the low-temperature hydrogen as the fuel, the heat resistance of the chip turbine can be dramatically improved. This allows
The inlet temperature can be further increased, and the cycle performance can be improved.

(B) Further, since the cooling gas is jetted downstream by the rotation of the chip turbine, the mixing of the driving gas and the intake air at the downstream is promoted. As a result, the combustion efficiency can be improved and the combustion distance can be shortened, so that the size of the engine body can be reduced.

(C) Further, since a part of the low-temperature hydrogen is used as cooling gas for cooling the chip turbine, heat exchange between the cooling gas and the chip turbine performed at that time causes
The heat exchange function can be partially substituted, and the heat exchanger for regenerating and heating low-temperature hydrogen can be downsized.

[Brief description of the drawings]

FIG. 1 is a schematic view showing an example of the structure of an ATR engine according to the present invention.

FIG. 2 is a sectional view specifically showing the structure of an ATR engine according to the present invention.

FIG. 3 is an enlarged sectional view of a main part of the ATR engine in FIG. 2;

FIG. 4 is a schematic view showing an example of the structure of a conventional ATR engine.

[Explanation of symbols]

 2 chip turbine 4 heat exchange unit 10 introduction path 17 gas flow path 22 through hole 23 moving blade 24 chip moving blade 25 moving blade side gas passage 26 chip stationary blade 27 moving blade side gas passage 28 cooling hole Hc cooling gas Hd driving gas

Claims (4)

[Claims] 1. A hydrogen gas generated by heating a low-temperature hydrogen supply source through a heat exchanging section and introduced as a driving gas into a tip turbine constituted by a tip rotor blade provided at a tip of the rotor blade. An air turbo ram engine for driving the rotor blades, wherein an introduction path is provided for introducing hydrogen gas bypassing the heat exchange section as cooling gas into the inside of the chip turbine. 2. A cooling hole for cooling the chip moving blade by discharging a cooling gas from the introduction path toward a flow path of the driving gas, wherein the chip moving blade is provided. Item 2. An air turbo ram engine according to item 1. 3. A blade-side gas passage through which the cooling gas from the introduction passage passes toward the chip stationary blade provided on the downstream side of the chip moving blade is provided in the chip moving blade. The air turbo ram engine according to claim 1 or 2, wherein: 4. A vane-side gas passage for passing cooling gas passing through the blade-side gas passage toward a chip vane provided downstream of the tip vane in the tip vane. The air turbo ram engine according to claim 3, wherein: