JP2019183826A - Turbine engine - Google Patents

Abstract

To provide a turbine engine capable of increasing the output.SOLUTION: In a turbine engine 100, air compressed by a compressor 112 is combusted in a combustor 118 to generate a combustion gas, a high-pressure stage power turbine 125 and a low-pressure stage power turbine 126 are rotated with the combustion gas, and the combustion gas is discharged. The high-pressure stage power turbine 125 and the low-pressure stage power turbine 126 are connected to an air turbine 131 via an output shaft 121, and the air turbine 131 is rotated with the compressed air generated by a gas generation compressor turbine section 110 to energize the output shaft 121. With this configuration, it is possible to provide a turbine engine capable of increasing the output.SELECTED DRAWING: Figure 1

Description

  The present invention is a turbine composed of two shafts, a turbine shaft for driving a compressor and a turbine shaft for taking out an output, to drive an air turbine arranged on the output shaft with air extracted from the compressor to urge the output shaft The present invention relates to a turbine engine characterized by increasing shaft output.

  Exhaust gas from the turbine that drives the output shaft of the turbine engine is released to the atmosphere, but energy still remains in this exhaust gas, and it can be said that it is uneconomical to release it to the atmosphere. If the energy of this exhaust gas can be recovered to improve the thermal efficiency, it will be possible to reduce fuel consumption and suppress harmful components into the atmosphere, which is beneficial not only for economic reasons but also for global warming prevention measures. A technique for improving the thermal efficiency by collecting the energy of the exhaust gas is called a regeneration cycle.

  The regeneration cycle uses a heat exchanger to exchange heat from the compressor with the exhaust gas heat, raising the temperature of the combustor inlet air, and saving the fuel that was conventionally used for raising the temperature. Cycle. The higher the air temperature at the combustor inlet, the higher the turbine inlet temperature and the better the thermal efficiency.

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  However, although the heat efficiency is improved in the regeneration cycle, there is a demerit that the output is not increased.

  The present invention has been made in view of such problems, and an object of the present invention is to provide a turbine engine capable of increasing the output.

  In order to solve the above-described problems, according to the present invention, a turbine engine that rotates and discharges a power turbine with combustion gas generated by combustion of air compressed by a compressor in a combustor, the compressor The compressor turbine shaft that drives the power turbine and the power turbine for taking out the output are connected to the air turbine at the output shaft, and the air turbine extracts the compressed air partially extracted during the compression by the compressor. A turbine engine is provided, which is heated by exhaust gas from a power turbine and driven by air having high temperature and pressure to urge the output shaft.

  According to this configuration, the power turbine is connected to the air turbine at the output shaft, and the air turbine is driven by the compressed air partially extracted during the compression performed by the compressor, and urges the output shaft of the power turbine. . Therefore, a turbine engine capable of increasing the output can be provided. The turbine engine is resistant to load fluctuations over a wide range and has high thermal efficiency.

  Furthermore, by providing the air turbine, in the conventional turbine engine, an output equivalent to that obtained by adding a power turbine using combustion gas can be obtained. Moreover, if the air turbine is a radiant flow type, power can be effectively converted between temperature and pressure.

The present invention can be applied in various ways. The following application examples can be appropriately combined.
For example, the suction negative pressure of the compressor may be used to discharge the air from the air turbine. Since the air at the outlet of the air turbine uses the suction negative pressure of the compressor, the pressure difference between the inlet and the outlet can be increased. Therefore, it is possible to effectively convert the temperature and pressure of the air supplied to the air turbine.

  A variable guide vane device that adjusts the distribution of the amount of working air that drives the air turbine and the amount of combustion air supplied to the compressor by an angle area according to an opening angle of the variable guide vane device; You may make it. Therefore, it is possible to control the air amount according to the load fluctuation by the variable guide vane device. For this reason, distribution of each turbine drive source of air and combustion gas can be controlled, and fuel consumption can be reduced over the entire load range. Further, since the amount of extraction can be adjusted so that the axial flow speed of the compressor does not become too low, surging does not occur.

  Further, a motor generator section may be installed between a compressor turbine shaft that supports the compressor and a guide cylinder that supports a gas generation turbine that drives the compressor. As described above, in the present invention, the motor generator section can be installed between the guide cylinder and the drive shaft of the compressor by providing the guide cylinder. Therefore, it is an auxiliary machine drive device provided in a conventional turbine engine, a power take-off gear provided on the core shaft of the compressor, a power take-off tower shaft from the core gear of the compressor, an accessory drive accessory, gear, There is no need to provide a box. For this reason, the whole turbine engine can be reduced in size. The electrification of the accessory drive device is called MME (More Electric Engine), and the degree of freedom of arrangement of the accessory drive device is improved. Therefore, it is possible to further reduce the total engine volume by improving the performance of the accessory driving device and rationalizing the arrangement.

  The inlet temperature of the air turbine may be raised by collecting the exhaust heat of the exhaust gas discharged from the power turbine. Conventional turbine engines always use fuel more than the required output even at low loads in order to ensure a stable operation that can cope with load fluctuations, and this is generally a factor of poor fuel consumption. On the other hand, according to the present invention, the air temperature at the inlet of the air turbine can be raised by heat recovery of the exhaust gas in which a large amount of energy remains. Therefore, the output of the air turbine is improved and the thermal efficiency of the engine is improved.

  The exhaust gas discharged from the power turbine is combusted by adding fuel to the combustion gas, and includes a working air heating unit that heats the working air of the combustor and the air turbine that generates the combustion gas. The output shaft may be energized by rotating with compressed air heated by the working air heating unit. By providing the working air heating unit, even when the load fluctuates, the required power can be dealt with in a short time whenever a large amount of power is required temporarily. In addition, if a bleed port and variable guide / vane device are provided on the high pressure side after compression, the fuel injection adjustment area will be expanded according to the load, and fuel consumption will be reduced over the entire load range, compared to conventional output machines. Is possible.

  In this way, the reheating device equipped with the working air heating unit does not add fuel to the compressed air from the atmosphere and burn it, but uses a gas that still has oxygen remaining after combustion, so a simple combustor A working air heating unit (including a fuel valve) may be used. This working air heating unit is derived from an afterburner of a jet engine, but a conventional burner uses combustion gas only for thrust. On the other hand, in the present invention, in the working air heating unit, the burner does not generate thrust but forcibly heats the bleed air from the compressor. When a variable guide / vane device is provided, the opening and closing of the variable guide / vane device is adjusted by the high-temperature air after heating, the inlet air of the combustor and the operating air amount of the air turbine are appropriately controlled, and the shaft output of the output shaft Can be increased.

  Moreover, you may make it heat the air compressed with the said compressor with the combustion gas from the said working air heating part, and supply it to the said air turbine. For this reason, the output of the air turbine is improved and the shaft output of the output shaft can be increased.

  Further, the combustion gas generated by the working air heating unit may be supplied to the inlet of the combustor. The amount of fuel added to the working air heating section is only an amount necessary for raising the inlet temperature of the combustor and is economical.

  A two-phase flow turbine connected to the output shaft; and a two-phase flow nozzle that heats the medium with combustion gas from the working air heating unit and separates the heated medium into a liquid phase and a gas phase. And the output shaft may be urged by rotating the two-phase turbine in the liquid phase. The exhaust gas after air heating in the reheat combustion by the working air heating part still has energy, and it is uneconomical to release to the atmosphere, but this exhaust gas heat is a gas that has already absorbed the temperature component and remains. Therefore, the gas temperature is as low as 70 to 250 ° C. The present invention uses a low-boiling point heat exchange medium such as R134a and R245fa to separate a low-temperature exhaust gas heat heating medium into a liquid phase and a gas phase with a two-phase flow nozzle, and rotates the liquid turbine with the liquid phase component. The engine output can be increased by energizing the output shaft of the engine.

  A medium condenser disposed between the outlet of the air turbine and the inlet of the compressor and condensing the liquid phase and the gas phase, the medium condenser being cooled by the passing air; It may be. The outlet medium of the two-phase flow turbine is a liquid / gas mixture, which is once cooled and liquefied by a medium condenser. The medium condenser is disposed between the outlet of the air turbine and the suction inlet of the compressor, and the cooling source is air passing between them, and a cooling fan can be dispensed with.

  In addition, a gas generation turbine that drives the compressor, a compressor turbine shaft that connects the compressor, a guide tube that supports the compressor turbine shaft, and a counter rotating mechanism, and the guide tube, The compressor, the core engine unit including the combustor, and the counter-rotating mechanism are separated from each other, and the counter-rotating mechanism includes a rear-stage power turbine to which combustion gas generated in the core engine unit is supplied, and A connecting shaft that connects a rear fan driven by the rear power turbine is a hollow shaft, and a front power turbine in which the working gas from the rear power turbine is supplied to the inside of the connecting shaft, and a front stage driven by the front power turbine. The solid shaft connecting the fan passes through coaxially, and the rotational direction of the rear power turbine and the front power turbine may be rotated in opposite directions. There. Also, at this time, the exhaust gas flow at the outlet of the preceding power turbine is taken out as thrust by a throttle duct that tapers toward the downstream, so that the entire amount of combustion gas generated by the afterburner is used in the preceding power turbine. You may do it.

  ADVANTAGE OF THE INVENTION According to this invention, it is possible to provide the turbine engine which can increase an output. Other effects of the present invention will also be described in a mode for carrying out the invention described later.

It is a figure for explaining the whole composition of turbine engine 100 concerning a 1st embodiment. It is a figure which shows the gas production | generation compressor turbine part 110. FIG. It is a figure for demonstrating the reproduction | regeneration cycle structure. It is a figure for demonstrating the whole structure of the turbine engine 200 which concerns on 2nd Embodiment. It is a figure for demonstrating a reburn cycle structure. It is a figure for demonstrating the whole structure of the turbine engine 300 which concerns on 3rd Embodiment. It is a figure for demonstrating a reburn regeneration cycle structure. It is a figure for demonstrating the whole structure of the turbine engine 400 which concerns on 4th Embodiment. It is a figure for demonstrating a front | former stage fan part, a back | latter stage fan part, a back | latter stage casing part, an engine main case, and a fan case. It is a figure which shows the turbine engine of the conventional turbo fan.

  Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings. In addition, in this specification and drawing, about the component which has the substantially same function structure, duplication description is abbreviate | omitted by attaching | subjecting the same code | symbol.

(First embodiment)
An overall configuration of the turbine engine 100 according to the first embodiment of the present invention will be described with reference to FIG. FIG. 1 is a front view for explaining the overall configuration of a turbine engine 100 according to the present embodiment. The turbine engine 100 of the present embodiment is used, for example, as a main engine for driving a rotor of a medium- or small-sized helicopter in a private sector, a power source in a fixed position configuration in land, sea, and air.

  The turbine engine 100 according to the present embodiment has a regeneration cycle structure, and includes three elements: a compressor, a combustor, and a turbine. The air sucked into the compressor generates combustion gas in the combustor and is discharged by turning the turbine. The turbine engine 100 is a combustion gas generated by burning the air compressed by the compressor 112 in the combustor 118, and rotates the power turbines 125 and 126, and the compressor drives the compressor 112. The turbine shaft 114-1 and the power turbines 125 and 126 that extract the output are connected to the air turbine 131 via the output shaft 121, and the air turbine 131 extracts the compressed air partially extracted during the compression by the compressor 112. Heated by the exhaust of the power turbines 125 and 126 and driven by air that has become high temperature and pressure, the output shaft 121 is energized.

  The turbine engine 100 includes a gas generation compressor turbine section 110 including a compressor and a combustor, a power turbine section 120 and an air turbine section 130 including a turbine, and a motor generator section 150. . Hereinafter, each component will be described.

(Gas generation compressor turbine section 110)
The gas generation compressor turbine section 110 will be described in detail with reference to FIG. FIG. 2 is a diagram illustrating the gas generation compressor turbine section 110. The gas generation compressor turbine section 110 includes a compressor 112, a compressor turbine 114, a turbine 116, and a combustor 118.

First, an outline of the gas generation compressor turbine section 110 will be described.
1) The gas generation compressor turbine section 110 is called a core engine section, and adds combustion fuel to compressed air obtained by compressing the taken-in air, and burns the combustion gas that rotates the power turbine section 120 by burning it. This is the part to be generated.
2) Combustion gas is generated by taking high-temperature and high-pressure air generated by an air compressor into the combustor main body 118-1, atomized fuel by the fuel valve 118-6, and air from the combustor air inlet 118-3. Combustion is performed in the combustor liner 118-2 of the combustor main body 118-1, and the obtained high-temperature gas is ejected from the combustor combustion gas outlet 118-4.
3) The high-temperature gas from the combustor combustion gas outlet 118-4 is rectified by the stationary blades of the gas generation turbine casing 116-2, sprayed onto the moving blades of the gas generation turbine 116-1, and rotates the gas generation turbine 116-1. .
4) The gas generation turbine 116-1 is connected by a compressor turbine shaft 114-1, and drives the air compressor 112-1. The air compressor 112-1 compresses air from the atmosphere and generates high-temperature and high-pressure air.
5) The hot gas from the combustor combustion gas outlet 118-4 passes through the gas generation turbine 116-1, and then rotates the power turbine unit 120.
6) The engine efficiency is the ratio of the remaining shaft output minus the fuel-generated gas generation energy.

  As shown in FIG. 2, the compressor 112 includes an air compressor 112-1, a compressor air inlet 112-2, a compressed air bleed port 112-3, a compressor air outlet 112-4, and a compressor. It is comprised from the casing 112-5.

  The air compressor 112-1 is an axial flow type multistage compressor. The axial flow type is a compressor that compresses while flowing air in the axial direction. The air compressor 112-1 has a configuration in which rotor blades are circumferentially attached to a compressor disk. The moving blades of the air compressor 112-1 are integrated with the disk (blade + disk = blisk) to reduce weight and reduce costs. The air compressor 112-1 is covered with a compressor casing 112-5 to form one stage, and the pressure is increased by stacking stages in the axial direction. The stationary blades are circumferentially arranged inside the case of the compressor casing 112-5.

  The compressor air inlet 112-2 takes air into the air compressor 112-1. As shown in FIG. 2, the air compressor 112-1 is provided on the side opposite to the combustor 118.

  The compressed air extraction port 112-3 extracts compressed air, and is connected to the compressor turbine 114 as shown in FIG.

  The compressor air outlet 112-4 discharges the air compressed by the air compressor 112-1 to the combustor 118. As shown in FIG. 2, the compressor air outlet 112-4 is provided at the end of the air compressor 112-1 on the combustor 118 side.

  As shown in FIG. 2, the compressor casing 112-5 accommodates an air compressor 112-1, a compressor air inlet 112-2, a compressed air bleed port 112-3, and a compressor air outlet 112-4. . A variable guide and vane device 133 is used in place of the surging-compatible variable stationary blade used in the conventional turbine engine.

  As shown in FIG. 2, the compressor turbine 114 includes a compressor turbine shaft 114-1, a compressor turbine bearing 114-2, a compressor turbine bearing seal 114-3, and a compressor turbine bearing fixing nut 114-. It is composed of four. The air compressor 112-1 is combined with the gas generation turbine 116-1 through the compressor turbine shaft 114-1 to become the compressor turbine 114.

  A guide tube 116-3 is disposed inside the compressor turbine shaft 114-1, and the compressor turbine bearing 114-2 and the compressor turbine bearing seal 114 are provided between the compressor turbine shaft 114-1 and the guide tube 116-3. -3 is assembled and fixed with a compressor turbine bearing fixing nut 114-4.

  As shown in FIG. 2, the turbine 116 includes a gas generation turbine 116-1, a gas generation turbine casing 116-2, and a guide tube 116-3. The gas generation turbine 116-1 is an axial flow type gas generation drive turbine. Combustion gas flows in the axial direction and flows to the power turbine section 120. The gas generation turbine 116-1 is configured by attaching moving blades circumferentially to a turbine disk. The rotor blades of the gas generation turbine 116-1 are implanted and assembled in a turbine disk. Since the moving blades of the gas generating turbine 116-1 are exposed to the high-temperature gas, they are cooled by the air extracted from the compressor 112.

  The gas generation turbine 116-1 is combined with the gas generation turbine casing 116-2 to constitute a one-stage power turbine. The stationary blades are circumferentially arranged inside the case of the gas generating turbine casing 116-2. The guide cylinder 116-3 is a fixed cylinder that does not rotate and is fixed to the walls of the gas generating turbine casing 116-2 and an air turbine casing 135 described later. The guide cylinder 116-3 isolates the core engine unit including the compressor 112 and the combustor 118 from the counter rotating mechanism.

  As shown in FIG. 2, the combustor 118 includes a combustor body 118-1, a combustor liner 118-2, a combustor air inlet 118-3, a combustor combustion gas outlet 118-4, and a combustor casing 118-5. And a fuel valve 118-6.

  The combustor body 118-1 includes an outer combustor liner 118-2 and an inner fuel valve 118-6, and the fuel valve 118-6 is disposed inside the combustor liner 118-2. The combustor liner 118-2 has a number of holes. The holes are arranged to be cooled with a laminar flow of air before combustion. A fuel valve 118-6 is disposed in the combustor liner 118-2 (not shown), and spark plugs are disposed on two or several fuel valves 118-6.

  The combustor main body 118-1 is circumferentially arranged inside the combustor casing 118-5 (this figure is a cannula type). A combustor body 118-1 is disposed between the air compressor 112-1 and the gas generation turbine 116-1, and is configured by being combined with a combustor casing 118-5. The fuel valve 118-6 has a function of spraying fuel in the form of a mist by pumping fuel from a fuel pump (not shown).

(Power turbine section 120)
The configuration of the power turbine unit 120 will be described with reference to FIG. FIG. 3 is a diagram for explaining the reproduction cycle structure. The structure of the power turbine unit 120 is the same as that of the turbine 116, but the rotation speed is different and the rotation direction is reverse rotation. As shown in FIG. 3, the power turbine unit 120 includes an output shaft 121, an output bearing 122, an output bearing seal 123, an output bearing fixing nut 124, a high pressure stage power turbine (power turbine) 125, and a low pressure stage. A power turbine (power turbine) 126, a power turbine casing 127, and a power turbine combustion gas outlet 128 are provided.

  The high-pressure stage power turbine 125 is a high-pressure stage axial flow turbine. The low-pressure stage power turbine 126 is a low-pressure stage axial turbine. The configurations of the high-pressure stage power turbine 125 and the low-pressure stage power turbine 126 will be described with reference to FIG. In the high-pressure stage power turbine 125 and the low-pressure stage power turbine 126, the rotor blades are circumferentially attached to the turbine disk. The blades of the high-pressure stage power turbine 125 and the low-pressure stage power turbine 126 are implanted and assembled in a turbine disk. The moving blades of the high-pressure stage power turbine 125 and the low-pressure stage power turbine 126 are exposed to the high-temperature gas, and are therefore cooled by the air extracted from the compressor. The high-pressure stage power turbine 125 and the low-pressure stage power turbine 126 are combined in a power turbine casing 127 to constitute a power turbine.

  Inside the case of the power turbine casing 127, the stationary blades are arranged in a circumferential shape. The output shaft 121 is configured by combining a high pressure stage power turbine 125 and a low pressure stage power turbine 126. The output shaft 121 passes through the guide tube 116-3, the output bearing 122 and the output bearing seal 123 are assembled between the guide tube 116-3 and the output shaft 121, and are fixed by the output bearing fixing nut 124.

(Air turbine part 130)
The configuration of the air turbine unit 130 will be described with reference to FIG. The air turbine section 130 includes an air turbine 131, a turbine air inlet 132, a variable guide vane device 133, a turbine air outlet 134, an air turbine casing 135, an air heater 136, a heater air inlet 137, Heater air outlet 138, heater casing 139, power turbine outlet cone 140, compressor bleed port / heater inlet pipe 141, heater outlet / air turbine inlet pipe 142, and combustion gas exhaust 143 And comprising.

  The air turbine 131 is driven by compressed air partially extracted during the compression by the compressor 112 and urges the output shaft 121. The air turbine 131 is a radial turbine, and working air flows in from the radial direction, blows to the impeller, and discharges to the atmosphere. As shown in FIG. 3, the air turbine 131 is configured such that blade blades are circumferentially integrated with a turbine disk. The air turbine 131 has a feature that it is lightweight and robust by integrated processing. The air turbine 131 is combined with an air turbine casing 135, and a variable guide vane device 133 is disposed at the turbine air inlet 132.

Here, the detail of the radiation turbine of the air turbine 131 is demonstrated.
Turbine drive energy Q = G · Cp · (Ti−T0) · ηt · (1-π) ^ (1-1 / κ)
G: Working gas flow rate, Cp: Gas constant pressure specific heat ratio, Ti: Turbine inlet temperature, T0: Atmospheric temperature, ηt: Turbine efficiency, π = P0 / Pi, P0: Turbine outlet pressure, Pi: Turbine inlet pressure, κ: Air From the specific heat ratio equation, the turbine work becomes larger as the turbine inlet temperature is higher and the outlet pressure is lower. The air turbine 131 suitable for high efficiency based on such a principle is considered to be a radial type. Since the air at the turbine air outlet 134 of the present embodiment is directly sucked into the compressor, the pressure at the turbine air outlet 134 can be made lower than that in the conventional open air type. For this reason, it is easy to obtain a high pressure difference. Since the air turbine 131 is driven by a small amount of bleed air during compression, the air turbine 131 is preferably a radiant flow type that is advantageous for pressure difference and temperature difference from the above formula principle rather than a large capacity axial flow type.

The above formula for the turbine drive energy will be further described.
In the formula, (1-1 / κ) is an exponent value of an exponential function of (1-pressure ratio), and this formula is a formula for generating power of the air turbine. Since a gas turbine generally uses isobaric pressure, a pressure component cannot be expected, and therefore a temperature difference component is mainly used. Therefore, the regeneration cycle of the conventional gas turbine improves heat efficiency by recovering heat from waste gas heat discarded to the atmosphere and reducing fuel consumption, but at this time, shaft output is not improved.

  In this embodiment, the shaft output can be improved when regenerating from waste heat. An air turbine is used to improve the shaft output. The power generated by the air turbine is mainly a pressure component rather than a temperature difference component. Therefore, the air turbine output is calculated by the described calculation formula using the specific heat ratio κ of air with respect to the pressure ratio of the pressure component. The work obtained by multiplying this by the mechanical efficiency as the turbine efficiency is the work that can be taken out. The feature of this embodiment is that the pressure difference can be increased compared to the conventional atmospheric discharge by arranging the working air outlet of the air turbine at the inlet of the gas turbine combustion air compressor. Although the fuel consumption does not change, the shaft output is improved, so if the shaft output is the same, the fuel consumption can be reduced.

  As shown in FIG. 3, the variable guide vane device 133 is provided at the turbine air inlet 132 and distributes the amount of working air that drives the air turbine 131 and the amount of combustion air supplied to the compressor 112. Adjust the angle area according to the vane opening angle. However, when the engine is running at low speed, priority is given to preventing surging of the compressor 112 by increasing the air flow rate in the front stage (increasing the axial flow speed).

  An air passage is formed spirally inside the air turbine casing 135. The output shaft 121 is disposed through the guide tube 116-3, and 20 and 21 are assembled between the guide tube 116-3 and the output shaft 121. An air turbine 131 is disposed on the front end side of the output shaft 121, and a high pressure stage power turbine 125 and a low pressure stage power turbine 126 are disposed on the other end side. After the output bearing 122 and the output bearing seal 123 are assembled, they are fixed by the output bearing fixing nut 124. .

  An air heater 136 is disposed on the circumference of the power turbine outlet cone 140 and is covered with a heater casing 139. The compressed air bleed port 112-3 and the heater air inlet 137 are connected by a compressor bleed port / heater inlet pipe 141, and between the turbine air inlet 132 and the heater air outlet 138 are the heater outlet / air. Piped by a turbine inlet pipe 142.

(Motor generator 150)
The motor generator 150 will be described with reference to FIG. 2 again. The motor generator unit 150 includes a motor generator rotor 151 and a motor generator stator 152. As shown in FIG. 2, the motor generator unit 150 includes a motor generator rotor 151 disposed inside the compressor turbine shaft 114-1 and a motor generator stator 152 disposed outside the guide cylinder 116-3. Configure the generator section.

  The motor generator rotor 151 is rotated by a permanent magnet, and the motor generator stator 152 generates magnetism by winding a copper wire coil around an iron core. The magnetism is converted into electric power by the motor generator stator 152 and connected to the external power supply controller and the battery from the motor generator stator 152 by wiring.

  The configuration of the turbine engine 100 has been described above. Hereinafter, the regeneration cycle operation / function of the turbine engine 100 will be described for each component with reference to FIG.

(Operation of Gas Generation Compressor Turbine Unit 110)
1) Atmosphere is sucked in from the compressor air inlet 112-2, air flows in the axial direction of the air compressor 112-1, and the air is pressurized in each stage.
2) High temperature and high pressure air enters the combustor body 118-1 and flows between the inside of the combustor body 118-1 and the outside of the combustor liner 118-2.
3) A number of holes are formed in the combustor liner 118-2, and air flows in a vortex through the holes into the container of the combustor liner 118-2.
4) A fuel valve 118-6 is disposed near the top of the combustor liner 118-2, and fuel is sprayed from the fuel valve 118-6.
5) The fuel valve 118-6 atomizes the fuel pumped from the external fuel pump and mixes fuel and air in the combustor liner 118-2.
6) At first, the mixture is ignited by an external electric spark, and a flame is generated.
7) Once ignited, the flame continues under a constant pressure and reaches a high temperature (about 1600 ° C. to 2000 ° C.), and is ejected from the combustor combustion gas outlet 118-4 shown in FIG. The gas generation turbine 116-1 is rotated by spraying the blades vigorously (approximately 1000 to 1400 ° C.).
8) The gas generation turbine 116-1 drives the air compressor 112-1 via the compressor turbine shaft 114-1 shown in FIG. 2 to generate high-temperature and high-pressure air.
9) The high-temperature and high-pressure gas that has passed through the gas generation turbine 116-1 is guided to the power turbine unit 120 shown in FIG.
10) The air flowing between the inside of the combustor body 118-1 and the outside of the combustor liner 118-2 flows to partially cool the combustor liner 118-2.

(Operation of the combustor 118)
Here, the operation of the combustor 118 will be described with reference to FIG. 2 in addition to FIG.
1) In the upstream portion of the combustor main body 118-1, about 25% of the air flow rate is surrounded by the combustor liner 118-2 so that the mixing ratio is about the air-fuel ratio (14 to 18: 1) from the turning guide vanes. Into the combustion area.
2) About 75% of the remaining air flow rate is used for internal cooling of the combustor main body 118-1, dilution of combustion gas, and secondary combustion of fuel that is not completely burned at about 25%.
3) The combustor liner 118-2 protected the flame from the air flow velocity (about 100 to 200 m / s) immediately before the combustor body 118-1, and was partially decelerated (about 10 to 20 m / s). Create a burning area.
4) Air flows between the combustor liner 118-2 and the combustor casing 118-5 and in the holes of the combustor liner 118-2, the amount of air flowing to the combustion region is adjusted, and the combustor liner 118-2 is also cooled. The
5) Fuel pressurized by a fuel pump (not shown) from the fuel valve 118-6 is sprayed from the nozzle and ignited by electric sparks at the start.
6) After ignition, the flame is maintained within the combustion zone by the following.
a) A primary combustion region is formed by mixing and burning air and fuel while forming a swirl vortex.
b) The secondary air flows into the downstream side of the primary combustion region from the hole of the combustor liner 118-2 to form the secondary combustion region.
c) An inflow of secondary air creates an annular vortex in the primary combustion region upstream of it.
The flame is sustained by the above.
7) In the secondary combustion region, the fuel that could not be combusted by the primary air is combusted, and the dilution by the secondary air starts together.
8) The rear part in the combustor liner 118-2 is a mixed dilution region where the primary and secondary air are mixed and the hot gases are averaged.
9) The primary combustion zone temperature immediately after combustion is about 2000 ° C., but is mixed and diluted with secondary air (60 to 130: 1) and immediately before the inlet of the gas generating turbine 116-1 to 1000 to 1400 ° C. (after 2000) ) To the extent that it can cope with the thermal stress failure of the rotor blades.

(Operation of the power turbine unit 120)
1) The combustion working gas that has passed through the gas generating turbine 116-1 is guided to the high-pressure stage power turbine 125 and rectifies and blows the gas flow onto the moving blades of the high-pressure stage power turbine 125.
2) The moving blades of the high-pressure stage power turbine 125 and the stationary blades of the power turbine casing 127 form a single row, and the gas flow rectification is performed by the stationary blades of the power turbine casing 127.
3) The rotor blades of the high-pressure stage power turbine 125 are cooled by the air extracted from the compressor, and durability at high temperatures is ensured.
4) The combustion working gas that has passed through the high-pressure stage power turbine 125 is guided to the low-pressure stage power turbine 126, and the gas flow is rectified and blown to the moving blades of the low-pressure stage power turbine 126.
5) The moving blades of the low-pressure stage power turbine 126 and the stationary blades of the power turbine casing 127 form a single row, and gas flow rectification is performed by the stationary blades of the power turbine casing 127.
6) The rotor blades of the low-pressure stage power turbine 126 are cooled by the air extracted from the compressor, and durability at high temperatures is ensured.
7) The shaft output rotation characteristic of the output shaft 121 is determined by the moving blade design value of the low-pressure stage power turbine 126.
8) Rotational power is extracted from the shaft end of the output shaft 121 by the rotation of the high-pressure stage power turbine 125 and the low-pressure stage power turbine 126.

(Operation of the air turbine unit 130)
The operation of the air turbine unit 130 will be described with reference to FIG. 3 in addition to FIG.
1) High temperature and high pressure air is extracted from the compressed air extraction port 112-3.
2) Before the extraction air is sent to the air turbine 131, the exhaust gas is regenerated and heated by the air heater 136, and the temperature is higher than that during extraction.
3) The bleed air is sent to the heater air inlet 137 of the air heater 136 via the compressor bleed port / heater inlet pipe 141.
4) The air heater 136 heats the extracted air with combustion gas exhaust heat, and exchanges heat with the exhaust heat gas.
5) The heated high-temperature high-pressure air is sent from the heater air outlet 138 to the turbine air inlet 132 of the air turbine 131 via the heater outlet / air turbine inlet pipe 142.
6) The working air from the turbine air inlet 132 is throttled by the nozzle of the variable guide vane device 133 and blown to the moving blades of the air turbine 131 to rotate the air turbine 131.
7) The rotation of the air turbine 131 is urged by the rotation of the output shaft 121 to increase the shaft output of the output shaft 121.
8) The amount of bleed air driven by the turbine is adjusted by adjusting the opening area of the nozzle vane of the variable guide vane device 133 disposed at the turbine air inlet 132.
9) The operating air temperature of the air turbine 131 needs to be higher than when the air is extracted (if it is low, regeneration is not possible).
10) When the turbine combustion temperature is low due to shaft output adjustment or the like and a sufficient temperature rise cannot be obtained from the exhaust gas, control is performed so as to stop the extraction by adjusting the opening degree.
11) The main points of the open / close control of the variable guide / vane device 133 in this cycle are as follows.
a) The regeneration air temperature must be higher than the extraction temperature.
b) When lower than the time of bleed, the bleed is stopped by closing the vane of the variable guide vane device 133.
c) Increase the efficiency of the air heater 136 and reduce the flow loss.
12) The working air adjusted by the variable guide vane device 133 passes from the turbine air inlet 132 along the rotated axial flow of the air turbine 131 to the compressor air inlet from the turbine air outlet 134 through the inside of the compressor casing 112-5. It flows to 112-2.
13) Since the air compressor 112-1 sucks air when the working air flows to the compressor air inlet 112-2, the working air at the turbine air outlet 134 is in a negative pressure state.
14) This structure has a merit that the turbine efficiency is greatly improved as compared with the case where the air turbine 131 alone releases from the turbine air outlet 134 to the atmosphere (which is higher than the atmosphere of about 2 atm).

  As described above, the compressed air partially extracted from the compressor air extraction port 112-3 disposed between the compressor air inlet 112-2 and the compressor air outlet 112-4 of the compressor 112 is compressed by the compressor. The exhaust gas is heated by the exhaust gas discharged by rotating the high-pressure stage power turbine 125 and the low-pressure stage power turbine 126 by the air heater 136 via the piping 141 between the extraction port / heater inlet. The high-temperature and high-pressure working air heated by the air heater 136 is sent to the turbine air inlet 132 of the air turbine 131 via the heater outlet / air turbine inlet pipe 142 to drive the air turbine 131.

(Operation of Regenerative Cycle Variable Guide / Vane Device 133)
When the engine load fluctuates, and the exhaust gas temperature becomes lower than the compression bleed temperature, particularly in a small load region, the heat exchange temperature may decrease, and cooling may occur contrary to the increase in heating. In such a case, the guide vane is squeezed in the closing direction by the variable guide vane device 133 to adjust the extraction amount. The guide vanes of the variable guide vane device 133 do not close completely so that they can respond immediately to load fluctuations, but are opened slightly to keep the air turbine 131 always in operation.

(Operation of motor generator unit 150)
The operation of the motor generator 150 will be described with reference to FIG. 2 in addition to FIG.
1) The engine is started by rotating the motor generator rotor 151 with external battery power and operating the compressor turbine shaft 114-1.
2) After the engine is started, power is generated between the motor generator rotor 151 and the motor generator stator 152 and electric power is taken out from the motor generator stator 152.
3) The generated power supplies power to the fuel, lubricant pump drive motor and others.
More Electric Engine = MEE greatly contributes to rationalization of engine components.
4) Engine weight reduction will be implemented by removing the following three conventional parts.
a) Power take-off gear provided on the high-pressure stage shaft b) Tower shaft for taking out power from the high-pressure stage shaft gear c) Accessory gear box for driving auxiliary equipment

(Effects of the first embodiment)
As described above, according to the present embodiment, the high pressure stage power turbine 125 and the low pressure stage power turbine 126 are connected to the air turbine 131 by the output shaft 121, and are discharged by the high pressure stage power turbine 125 and the low pressure stage power turbine 126. The compressed air partially extracted from the core engine unit 110 is heated by the heat of the working gas, and the air turbine 131 is rotated by this working air to urge the output shaft 121. Therefore, it is possible to provide the turbine engine 100 capable of increasing the output. The turbine engine 100 is resistant to load fluctuations over a wide range and has high thermal efficiency.

  Furthermore, by providing the air turbine 131, an output equivalent to that obtained by adding a power turbine using combustion gas in a conventional turbine engine can be obtained. In addition, if the air turbine 131 is a radiant flow type, power can be effectively converted between temperature and pressure.

  Further, in order to ensure stable operation that can always cope with load fluctuations, the conventional turbine engine uses fuel more than the required output even at low load, which is generally a factor of poor fuel consumption. On the other hand, in the present embodiment, the air temperature at the inlet of the air turbine 131 can be raised by heat recovery of the exhaust gas in which a large amount of energy remains. Therefore, the output of the air turbine 131 is improved and the thermal efficiency of the engine is improved.

  Moreover, since the air at the outlet of the air turbine 131 uses the suction negative pressure of the compressor 112, the pressure difference between the inlet and the outlet can be increased. Therefore, the power and temperature of the air supplied to the air turbine 131 can be effectively converted.

  Further, a variable guide / vane device 133 that adjusts the distribution of the amount of working air that drives the air turbine 131 and the amount of combustion air that is supplied to the compressor 112 by an angle area according to the opening angle of the variable guide / vane device 133. Since the variable guide and vane device 133 is provided, it is possible to control the air amount according to the load fluctuation. For this reason, distribution of each turbine drive source of air and combustion gas can be controlled, and fuel consumption can be reduced over the entire load range. Further, since the amount of extraction can be adjusted so that the axial flow speed of the compressor 112 does not become too low, surging does not occur.

  Further, by providing the guide cylinder 116-3, the motor generator unit 150 can be installed between the guide cylinder 116-3 and the drive shaft of the compressor 112. Therefore, it is an auxiliary machine drive device provided in a conventional turbine engine, a power take-off gear provided on the core shaft of the compressor, a power take-off tower shaft from the core gear of the compressor, an accessory drive accessory, gear, There is no need to provide a box. For this reason, the whole turbine engine can be reduced in size. The electrification of the accessory drive device is called MME (More Electric Engine), and the degree of freedom of arrangement of the accessory drive device is improved. Therefore, it is possible to further reduce the total engine volume by improving the performance of the accessory driving device and rationalizing the arrangement.

  In addition, the temperature of the inlet of the air turbine 131 is raised by recovering the exhaust heat of the exhaust gas discharged from the high pressure stage power turbine 125 and the low pressure stage power turbine 126, so that the output of the air turbine 131 can be improved. .

(Second Embodiment)
A turbine engine 200 according to a second embodiment will be described with reference to FIGS. 4 and 5. FIG. 4 is a diagram for explaining the overall configuration of the turbine engine 200 according to the present embodiment. FIG. 5 is a diagram for explaining a reburn cycle structure. The turbine engine 200 of the present embodiment has a reheat cycle structure, and differs from the first embodiment in that a reburn cycle is provided instead of the regeneration cycle configuration of the first embodiment. Is the same as in the first embodiment. Hereinafter, the working air heating unit 210 different from the first embodiment will be mainly described. Constituent elements having substantially the same functional configuration are denoted by the same reference numerals, and redundant description is omitted. The turbine engine 200 of the present embodiment is used for, for example, a military helicopter, a rotor driving main engine of a large civil helicopter, a power source in a fixed position configuration in land, sea and air.

  As shown in FIG. 4, the turbine engine 200 is configured by providing a working air heating unit 210 in a gas generation compressor turbine unit 110, a power turbine unit 120, and a motor generator unit 150. That is, instead of the air heater 136, the heater air inlet 137, the heater air outlet 138, the heater casing 139, and the combustion gas exhaust port 143 of the air turbine unit 130 constituting the regeneration cycle of the first embodiment, the operation is performed. A reburning cycle configuration comprising the air heating unit 210 is provided.

  The working air heating unit 210 heats the working air of the air turbine 131. The air turbine 131 rotates with the compressed air heated by the working air heating unit 210 and urges the output shaft 121. As shown in FIG. 5, the working air heating unit 210 includes a pilot burner 211, a flame holder 212, a reheat combustor 213, a reheat combustor casing 214, a reheat heat exchanger 215, A combustion gas exhaust port 216 and a compressed air extraction port 217 are provided.

  As shown in FIG. 5, the working air heating unit 210 bleeds high-pressure compressed air from the middle of compression of the compressor at the compressed air bleed port 217, and heat-exchange heats with reheat combustion gas in the reheat heat exchanger 215. To do. The working air heating unit 210 adjusts the opening degree of the variable guide vane device 133 according to the engine load. When the engine output is large, the temperature of the working air is increased by heating with the combustion gas added with fuel, and the opening degree of the variable guide vane device 133 is decreased. Further, when the engine output is small, fuel addition is not performed, the working air is heated and heated with the heat of the exhaust gas, and the opening degree of the variable guide vane device 133 is increased.

  As shown in FIG. 5, the working air heating unit 210 includes a pilot burner (working air heating unit combustor) 211, a flame holder 212, a reheat combustor 213, a reheat combustor casing 214, The reheat heat exchanger 215, the combustion gas exhaust port 216, and the compressed air extraction port 217 are configured. Pilot burner 211, flame holder 212, reheat combustor 213, reheat combustor casing 214, and reheat heat exchanger 215 are disposed downstream of power turbine combustion gas outlet 128. Hereinafter, each component will be described with reference to FIG.

  The pilot burner 211 creates a fire by electric ignition, and blows fuel from the burner fuel valve to the fire to create a burner flame. Exhaust gas discharged from the high pressure stage power turbine 125 and the low pressure stage power turbine 126 is supplied to the inlet of the pilot burner 211. The flame holder 212 keeps the combustion stable and prevents the fire from extinguishing. The reheat combustor 213 is covered with a reheat combustor casing 214, and a reheat heat exchanger 215 is disposed in the reheat combustor casing 214, and the operating air is heated by heat exchange.

  The combustion gas exhaust port 216 discharges the combustion gas to the atmosphere. The compressed air bleed port 217 and the reheat heat exchanger 215 are the compressor bleed port / heater inlet pipe 141, and the reheat heat exchanger 215 and the turbine air inlet 132 are the heater outlet / air turbine inlet pipe 142. The working air piping is arranged via

  The configuration of the working air heating unit 210 has been described above. Hereinafter, the reburning cycle operation of the turbine engine 200 will be described with reference to FIG.

1) The opening degree of the variable guide vane device 133 is adjusted according to the engine load.
2) High-pressure air that is being compressed by the compressor is extracted from the compressed air extraction port 217, and the reheat heat exchanger 215 raises the temperature by reheat heating.
3) At high engine load:
After the working air is heated with the combustion gas added with fuel, the opening degree of the variable guide vane device 133 is increased to increase the output of the air turbine 131. The engine output increases, and the opening of the variable guide vane device 133 decreases. The reason why the opening degree of the variable guide vane device 133 is reduced will be described. The amount of bleed air is suppressed, the combustion air is increased, and the shaft output of the power turbine unit 120 is increased. The working air is superheated by the fuel-added combustion gas as much as the amount of extraction is suppressed, and the shaft output of the air turbine unit 130 increases.
4) At low engine load:
After heating the working air with exhaust gas heat without adding fuel, the air turbine 131 is turned. The engine output decreases and the opening degree of the variable guide vane device 133 increases. The reason why the opening degree of the variable guide vane device 133 is increased will be described. This is to prevent surging by increasing the front air flow rate (increasing the axial flow velocity).

Here, the operation principle of the reheat combustion chamber will be described.
1) The combustion chamber of the turbine engine 200 is divided into a primary combustion region and a secondary combustion region.
2) The primary air-fuel ratio is 14 to 18: 1 in the air: fuel ratio, and the combustion temperature is 1600 to 2000 ° C.
Secondary is 60-130: 1, combustion temperature 700-1200 ° C. In the 21st century, it is 1000-1400 ° C.
Combustor outlet = turbine inlet temperature is determined by the heat resistance limit value of the turbine blade in continuous use at high temperatures.
3) A large amount of air is sucked in from the air necessary for combustion, and a part of the air is used, and the blades and the combustor main body 118- of the gas generating turbine 116-1, the high pressure stage power turbine 125, and the low pressure stage power turbine 126 in the high temperature section 1 and the combustor liner 118-2 are cooled, and the air is exhausted around the exhaust port of the combustion gas exhaust port 143.
4) The exhaust gas that has passed through the gas generation turbine 116-1, the combustor main body 118-1, the combustor liner 118-2, the high-pressure stage power turbine 125, and the low-pressure stage power turbine 126 is about 75% of the intake air. Oxygen remains.
5) When the fuel is again injected into the high-temperature exhaust gas with sufficient oxygen left, high-temperature combustion gas can be generated.
6) Recombustion is performed by forming a fire type with the burner flame of the pilot burner 211 and mixing this burner flame with exhaust gas. In addition, flame is held by the flame holder 212 so that the fire does not disappear and is continuously burned. The pilot burner 211 may be constantly ignited.

(Effect of 2nd Embodiment)
As described above, according to the present embodiment, since the working air heating unit 210 is provided, even if the load fluctuates, the required power can be dealt with in a short time whenever a large amount of power is required temporarily. In addition, if the bleed port and variable guide / vane device 133 are provided on the high pressure side after compression, the fuel injection adjustment range corresponding to the load is expanded compared to the conventional output machine, and fuel consumption is improved in the entire load range. Reduction is possible.

  In addition, the reheat device provided with the working air heating unit 210 does not add fuel to the compressed air from the atmosphere and burn it, but uses a gas that still has oxygen remaining after combustion, so a simple combustor The working air heating unit 210 (including the fuel valve) may be used. This working air heating unit 210 is derived from an afterburner of a jet engine, but a conventional burner uses combustion gas only for thrust. On the other hand, in this embodiment, the burner of the working air heating unit 210 does not generate thrust but forcibly heats the bleed air from the compressor 112. When the variable guide / vane device 133 is provided, the opening / closing of the variable guide / vane device 133 is adjusted by the high-temperature air after heating, the inlet air of the combustor 118 and the operating air amount of the air turbine 131 are appropriately controlled, and output The shaft output of the shaft 121 can be increased.

  Further, since the air compressed by the compressor 112 is heated by the combustion gas from the working air heating unit 210 and supplied to the air turbine 131, the output of the air turbine 131 is improved, and the shaft output of the output shaft 121 is increased. Can be increased.

  Further, since the combustion gas generated in the working air heating unit 210 is supplied to the inlet of the combustor 118, the amount of fuel added to the working air heating unit 210 increases the inlet temperature of the combustor 118. Only the amount needed is economical.

(Third embodiment)
A turbine engine 300 according to a third embodiment will be described with reference to FIGS. 6 and 7. FIG. 6 is a diagram for explaining the overall configuration of the turbine engine 300 according to the present embodiment. FIG. 7 is a diagram for explaining a reburn regeneration cycle structure. The turbine engine 300 of the present embodiment has a reheat regeneration cycle structure, and the working medium heating unit 310, the two-phase flow nozzle unit 320, the two-phase flow turbine unit 330, and the working medium are added to the turbine engine 200 of the second embodiment. The second embodiment is different from the second embodiment in that a reburn regeneration cycle including a condenser unit 340 and a medium pump unit 350 is provided, and other configurations are the same as those in the second embodiment. Hereinafter, a description will be given focusing on differences from the second embodiment. Constituent elements having substantially the same functional configuration are denoted by the same reference numerals, and redundant description is omitted. The turbine engine 300 of the present embodiment is used for a power source such as a high-speed boat, a railway vehicle (including a motor drive after power generation), a power source in a fixed position configuration in land, sea, and air.

  The turbine engine 300 of the present embodiment has a reburn regeneration cycle structure. As shown in FIG. 6, the turbine engine 200 of the second embodiment includes a working medium heating unit 310 that constitutes a reburn regeneration cycle, and a two-phase flow. A nozzle unit 320, a two-phase flow turbine unit 330, a working medium condenser unit 340, and a medium pump unit 350 are added.

First, the outline of the turbine engine 300 will be described.
1) The turbine engine has lower thermal efficiency than diesel. However, the exhaust heat temperature is high.
Diesel thermal efficiency is about 40% to 50%, and turbine thermal efficiency is about 30% to 35%.
Diesel exhaust heat temperature is about 250 ° C to 300 ° C, and turbine exhaust heat temperature is about 500 ° C to 600 ° C.
2) In the reheat cycle of the turbine engine 200 of the second embodiment, in addition to the main combustion, fuel is further injected so that heat recovery can be performed from the exhaust heat energy to improve the final heat efficiency.
3) The combustion gas used in the reheat cycle of the turbine engine 200 is released to the atmosphere after sufficiently heating the working air. For this reason, the exhaust heat temperature after use for heating and heating the working air is low.
4) In order to recover power from an exhaust heat temperature of about 70 ° C. to 250 ° C., it is necessary to interpose a low-boiling working medium in heat exchange with the heat source.
5) As the low boiling point medium, for example, alternative fluorocarbons such as R134a and R245fa can be used.
6) In the power recovery method, after heating the low-temperature medium, the thermal energy is converted into kinetic energy via the two-phase flow nozzle unit 320, sprayed on the blades of the two-phase flow turbine 331 (impulsive turbine), and the output shaft 121 is energized. Do that.
7) The working medium upstream of the two-phase flow nozzle 321 is a liquid, and the liquid is converted into a two-phase flow through the two-phase flow nozzle 321.
8) The two-phase flow turbine 331 directly rotates and rotates the two-phase flow, not the steam, on the rotor blades of the two-phase flow turbine 331, energizes the output shaft 121, and is condensed and cooled by the working medium condenser unit 340. A heat cycle is formed by being sent to the working medium heating unit 310 by the unit 350.

  The overview of the turbine engine 300 has been described above. Hereinafter, the structure of each component of the reburn regeneration cycle structure of the turbine engine 300 that is characteristic of the present embodiment will be described.

(Working medium heating unit 310)
The working medium heating unit 310 heats the medium by exchanging heat between the high-pressure medium and the combustion gas exhaust heat. As shown in FIG. 7, the working medium heating unit 310 includes a medium heater 311, a heater medium inlet 312, a heater medium outlet 313, a medium heater casing 314, a combustion gas exhaust port 315, a medium And a heater outlet / two-phase flow nozzle inlet pipe 316. A high-pressure medium is pumped from the two-phase flow turbine outlet / condenser inlet pipe 345 to the heater medium inlet 312 of the medium heater 311, and heat is exchanged with combustion gas exhaust heat in the medium heater casing 314 to heat the medium. The medium is sent from the heater medium outlet 313 to the two-phase flow nozzle section 320 via the medium heater outlet / two-phase flow nozzle inlet pipe 316.

(Two-phase flow nozzle part 320)
The two-phase flow nozzle unit 320 generates an equilibrium homogeneous two-phase flow from the medium from the working medium heating unit 310. As shown in FIG. 7, the two-phase flow nozzle unit 320 includes a two-phase flow nozzle 321, a nozzle medium inlet 322, and a nozzle medium outlet 323. The medium exiting the medium heater 311 is guided to the two-phase flow nozzle 321 in a pressurized liquid state, expands in the two-phase flow nozzle 321, forms a two-phase flow jet, and drives the two-phase flow turbine 331. The two-phase flow nozzle 321 generates a balanced homogeneous two-phase flow with a small gas-liquid velocity difference while ensuring a sufficient mass flow rate. The two-phase flow generation by the two-phase flow nozzle 321 is performed by expanding the pressurized and heated medium with a tubular nozzle without vaporizing the medium and evaporating a part thereof.

  The function of the two-phase flow nozzle 321 is to effectively convert the thermal energy of the working medium into kinetic energy. For this purpose, it is necessary to make the droplets as uniform and fine as possible. In the uniform refinement, the gas phase divides the liquid phase into fine droplets from the nozzle medium inlet 322 to the nozzle medium outlet 323 of the two-phase flow nozzle 321, and the momentum of the gas phase is transmitted to the droplets. At the nozzle medium outlet 323, the flow velocity of the gas phase and the liquid phase is made uniform by accelerating the fine droplets by kneading the gas phase and the liquid phase.

(Two-phase turbine section 330)
The two-phase flow turbine section 330 includes a two-phase flow turbine 331, a turbine medium inlet 332, a turbine medium outlet 333, a two-phase flow turbine casing 334, a turbine casing seal 335, and a two-phase flow nozzle outlet / two-phase flow. A turbine inlet pipe 336, a turbine cutoff valve 337, and a turbine adjustment valve 338 are provided.

  The medium from the two-phase flow nozzle section 320 flows from the turbine medium inlet 332 through the two-phase flow turbine casing 334 to the turbine medium outlet 333, and the two-phase flow turbine 331 generates rotational power. A turbine casing seal 335 is provided so that the medium passing through the two-phase flow turbine casing 334 does not leak, and a turbine shut-off valve 337 and a turbine regulating valve 338 are disposed in front of the turbine medium inlet 332. The turbine cutoff valve 337 is shut off and the turbine adjustment valve 338 is adjusted in accordance with the presence or absence of fuel injection in the pilot burner 211 and the load fluctuation caused by the output adjustment of the output shaft 121.

  Here, the two-phase flow turbine 331 of the present embodiment will be briefly described. In the two-phase flow of gas and liquid, the two-phase flow turbine 331 squeezes the two-phase flow with the two-phase flow nozzle 321 and separates it into gas and liquid, and rotates the two-phase flow turbine 331 with the liquid component therein. The two-phase turbine 331 becomes a turbine of a water turbine using the separated liquid. The two-phase flow turbine 331 uses a turbine called an impulse turbine that takes liquid in an impulsive manner when the liquid is directly taken into the blades of the turbine. The power work to turn the water turbine is to turn the water turbine with the liquid component of the gas-liquid two-phase flow pressurized by the pressure pump, but at this stage the turbine rotational force and the pressure pump driving force are balanced and the work that can be taken out to the outside is zero become.

  In order to extract the power to the outside by the system of the present embodiment configured as described above, in this balanced state, the temperature component of the engine exhaust gas heat conventionally discarded to the atmosphere is recovered by the heat exchanger, and this recovery is performed. The liquid component at the time of separation by the two-phase flow nozzle 321 is accelerated by the temperature component thus obtained. The acceleration of the liquid due to the recovered heat temperature is the work that can be taken out. Since the exhaust gas temperature released to the atmosphere is low, a low boiling point medium that can cope with the low exhaust gas temperature is used. The gas-liquid two-phase flow of the present embodiment is a two-phase flow of a low-boiling-point medium liquid and air gas, and the low-boiling-point medium liquid rotates the two-phase flow turbine 331, that is, the low-boiling point liquid turbine. The liquid after turbine rotation is returned to the gas-liquid two-phase flow by the working medium condenser section 340 so that the heat can be recovered again. The cooling medium heat source of the working medium condenser unit 340 uses the compressor inlet air of the main body.

(Working medium condenser section 340)
The working medium condenser section 340 includes a medium condenser 341, a condenser medium inlet 342, a condenser medium outlet 343, a medium tank 344, a two-phase flow turbine outlet / condenser inlet pipe 345, and a condenser outlet. / Medium tank inlet pipe 346.

  The working medium condenser section 340 cooling source is characterized by air cooling using the flow of exhaust air from the air turbine 131 and the suction air from the air compressor 112-1. Between the medium condenser 341 and the two-phase flow turbine outlet / condenser inlet pipe 345, the two-phase flow turbine outlet / condenser inlet pipe 345, and the condenser medium outlet 343 via the condenser outlet / media tank inlet pipe 346. Piped.

(Medium pump unit 350)
The medium pump unit 350 includes a medium pump 351, a pump medium inlet 352, a pump medium outlet 353, a medium tank outlet / medium pump inlet pipe 354, a medium pump outlet / medium heater inlet pipe 355, a pump / An inter-turbine bearing 356 and a pump / turbine bearing seal 357 are provided.

  The medium that has become liquid in the medium condenser 341 is sent to the working medium heating unit 310 by the medium pump 351 through the pipe 345 between the two-phase flow turbine outlet / condenser inlet. In order to maintain the liquid phase state at the heater medium outlet 313, the medium pump 351 is required to have a high head. Between the two-phase flow turbine outlet / condenser inlet pipe 345 and the pump medium inlet 352 is a medium tank outlet / media pump inlet pipe 354, and between the pump medium outlet 353 and the heater medium inlet 312 is a medium pump outlet / medium heater inlet. Piping is performed via the inter-pipe 355.

  The configuration of the turbine engine 300 has been described above. Hereinafter, the operation of the turbine engine 300 will be described with reference to FIGS. 6 and 7.

(Starting of turbine engine 300: turbine bypass operation)
The medium pump 351 sucks the medium from the two-phase flow turbine outlet / condenser inlet pipe 345 and monitors the rotation speed of the medium pump 351 so as to maintain the pressure of the heat medium so that the medium does not evaporate in the medium heater 311. Then, the turbine shut-off valve 337 is fully closed, the turbine adjustment valve 338 is fully opened, and the turbine bypass operation is performed.

(Starting of the two-phase flow turbine section 330)
For example, when the medium temperature is 90 ° C. or higher, the turbine cutoff valve 337 is fully closed and the turbine adjustment valve 338 is fully opened.

(Operation of the two-phase flow turbine unit 330)
The flow rate and pressure of the medium are adjusted by adjusting the opening of the turbine adjustment valve 338.

(Stop of two-phase flow turbine section 330)
The flow rate switching from the turbine adjustment valve 338 to the turbine shut-off valve 337 is performed gradually, and the mode shifts to the turbine bypass operation mode.
At the same time as the rotation (engine) of the output shaft 121 is stopped, the turbine shut-off valve 337 is closed.

Here, the details of the impulse turbine of the two-phase flow turbine will be described.
1) In the impulse turbine of the two-phase flow turbine 331, the liquid phase component in the two-phase flow blown to the turbine blades flows by forming a layer on the cover surface of the blades by centrifugal force.
2) For the Wg fluid, rotate the blades at the circumferential speed U with F = W / g * (C1 * cos α−C2 * cos δ).
F is a force at which the two-phase flow velocity C is applied to the turbine blades at a fixed angle α (about 15 to 20 °). 3) Two-phase liquid = 1, gas = mass flow rate at the compressor air inlet 112-2 M, flow rate V to C = (M1 * V1 + M2 * V2) / (M1 + M2)
However, the angle δ of C2 is δ = 90−α °.
4) Since the two-phase flow turbine 331 is directly connected to the output shaft 121, the peripheral speed U of the two-phase flow turbine 331 is adjusted by the turbine adjusting valve 338 so that the working fluid flow velocity and flow rate can be synchronized with the low-pressure stage power turbine 126. adjust.

The performance index of the turbine engine 300 will be described.
The performance index of the turbine engine 300 includes specific power and thermal efficiency.
1) Specific power is the power that can be taken out per unit flow rate of gas flowing into the engine.
2) If the specific output is large, the same power can be generated with a smaller amount of working fluid, resulting in a small and large output engine.
3) To increase the specific output, increase the ratio of the turbine inlet combustion gas temperature to the atmospheric temperature.
4) Since the high temperature of the working gas is determined by the melting point of the turbine material, measures are taken so that it can be operated at a temperature exceeding the melting point of the material by air cooling of the rotor blades or heat-resistant coating.
5) Thermal efficiency is the ratio of power that can be extracted from the thermal energy of fuel.
6) Thermal efficiency = [taken out power] / [thermal energy of fuel]

(Effect of the third embodiment)
As described above, according to the present embodiment, the exhaust gas after the air heating in the reheat combustion by the working air heating unit 210 still has energy, and the atmospheric emission is uneconomical. Since heat is a gas that has already absorbed the temperature component and remains, the gas temperature is as low as about 70 to 250 ° C. The present invention uses a low-boiling point heat exchange medium such as R134a and R245fa to separate a low-temperature exhaust gas heat heating medium into a liquid phase and a gas phase with a two-phase flow nozzle 321 and rotates a liquid turbine with the liquid phase component. The engine output can be increased by energizing the output shaft 121 of the turbine engine.

  The outlet medium of the two-phase flow turbine is a liquid / gas mixture, which is once cooled and liquefied by the medium condenser 341. The medium condenser 341 is disposed between the outlet of the air turbine 131 and the suction inlet of the compressor 112, and the cooling source is air passing between them, so that a cooling fan can be omitted.

(Fourth embodiment)
The turbine engine 400 according to the fourth embodiment is a turbine engine called a turbo fan that generates thrust by a fan of an aircraft propulsion generating prime mover (hereinafter, turbo fan = conventional diagram is shown in FIG. 10). The turbine engine according to the present embodiment is characterized in that the propulsion fan is driven by the combustion gas from the core engine, fuel is added again to the exhaust gas after driving, and a further fan-driven turbine is rotated. It is. The turbine engine 400 includes two sets of thrust generating fans, and the shafts of the sets rotate on the same axis in opposite directions. This is achieved by this embodiment and is called a counter-rotating fan. 2. Description of the Related Art Conventionally, an aircraft thrust generating device is known that obtains a propulsive force by rotating two sets of propellers in the opposite directions on the same axis, which is called a double reversing propeller. No turbo fan with counter-rotating fan thrust is currently available (2018).

Here, a conventional turbo engine called a turbo fan will be described.
It is well known that turbo-fans are widely used at present (2018), called jet engines for aircraft propulsion power units, regardless of civilian or military use. The ratio of the propulsion amount by the fan and the propulsion amount by the combustion gas is called a bypass ratio. A bypass ratio of 5 to 10 or more is called a high bypass ratio and is frequently used in medium and large passenger aircraft. A bypass ratio of 1 or less is called a low bypass ratio and is often used in military fighters. Aircraft using turbo fans recently (after 2018) tend to be as follows.

  (1) In the field of business jets (especially from 10 to 15 passengers / passengers), the flight range has increased (for example, 2000 km or more), and it has become possible to move directly overseas, bothering to international airlines. There is no need to move overseas. Therefore, the time required for movement is greatly shortened and the business can be more specialized.

(2) In the field of military jets, especially jet fighters, with the recent improvement in information processing capabilities, there will be no obstacles to combat even if the maximum speed during fighter aircraft movement is not increased to Mach 2 (M2) or higher. For example, it is said that even if the maximum speed during battle is M1.6, sufficient fighter maneuvering is possible. Therefore, if there is no need for a thrust booster called a conventional afterburner that consumes a large amount of fuel, the combat action radius is expanded with less fuel.
Further, the conventional contra-rotating propeller for aviation needs to incorporate a reverse gear in the transmission and to configure each of the clockwise and counterclockwise rotating shafts on the same axis, and has the following problems.
1) If the centers of the rotation axes of the two propellers are not matched, severe vibration will occur.
2) The durability of the main body is greatly reduced due to severe vibration. Since the gear box of the transmission incorporates a gear mechanism that is nearly twice as large as the device without the double reversing mechanism, the fatal weight increases for aircraft due to the necessity of the mechanism.

  A turbo engine that can provide the above needs with a bypass ratio of 1 or more and 5 or less is expected as a new field. However, as shown in FIG. 10, a conventional turbo engine called a turbo fan has poor fuel efficiency and lack of thrust in the same size. Is an issue. Therefore, in view of the recent market demand for turbofan engines such as (1) and (2) above, we provide a turbo engine that is a fuel-efficient, high-thrust and lightweight counter-rotating turbofan that can meet these needs. To do.

First, consider a fan bypass ratio that can accommodate the following (1) and (2).
(1) The flight distance that allows direct overseas travel is set to 2000 km to 4000 km.
Reason: Indicates the case where the flight distance necessary for movement between capital cities is calculated.
(2) The travel time needs to be significantly shortened and the operation speed is set to 1200 km / h.
Reason: The amount of fuel loaded is less than or equal to the conventional, and the current international speed is 800 x 1.5 times. It is considered that the 3rd to 4th place of the bypass ratio that can cope with (1) 4000 km and (2) 1200 km / h is effective.

  In this embodiment, a turbine engine of a counter-rotating turbo fan is provided as a low fuel consumption, high thrust, lightweight aviation turbo fan corresponding to the above concept. A turbine engine 400 according to this embodiment will be described with reference to FIGS. 8 and 9. FIG. 8 is a diagram for explaining the overall configuration of the turbine engine 400 according to the present embodiment. FIG. 9 is a view for explaining the front fan unit, the rear fan unit, the rear casing unit, the engine main case, and the fan case. Hereinafter, a description will be given focusing on differences from the first embodiment. Constituent elements having substantially the same functional configuration are denoted by the same reference numerals, and redundant description is omitted.

  The turbine engine 400 has a counter rotating turbo fan structure. As shown in FIG. 8, the turbine engine 400 includes a gas generation turbine 116-1 that drives the compressor 112, a guide cylinder 116-3 that supports the compressor turbine shaft 114-1 that connects the compressor 112, and two And a double reversing mechanism. The guide tube 116-3 separates the core engine unit 110 including the compressor 112 and the combustor 118 from the counter rotating mechanism. The contra-rotating mechanism includes a front fan section 410, a rear fan section 430, a rear casing section 460, an engine main case 470, and a fan case 450. In the contra-rotating mechanism, the connecting shaft 433 that connects the rear-stage power turbine 438 to which the combustion gas generated in the core engine unit is supplied and the rear-stage fans 431 and 432 driven by the rear-stage power turbine 438 is a hollow shaft. A front stage fan drive shaft (solid shaft) 412 that connects the front stage power turbines 419 and 420 to which the working gas from the rear stage power turbine 438 is supplied into the shaft 433 and the front stage fan 411 driven by the front stage power turbines 419 and 420. Passes through the same axis, and rotates the rotation directions of the rear power turbine 438 and the front power turbines 419 and 420 in opposite directions. The air flow at the outlet of the rear fan unit 430 is taken out as thrust by a throttle duct that tapers toward the downstream. The entire amount of the combustion gas generated by the afterburner is used in the front-stage high-pressure power turbine 419 and the front-stage low-pressure power turbine 420 that drive the front-stage low-pressure fan 411, and the exhaust at the outlets of the front-stage high-pressure power turbine 419 and the front-stage low-pressure power turbine 420. The gas is taken out as thrust by the total jet restrictor duct 463 that tapers as it goes downstream.

(Front fan section 410)
1) The front-stage low-pressure fan 411, the front-stage high-pressure stage power turbine 419, and the front-stage low-pressure stage power turbine 420 are coupled by a front-stage fan drive shaft (solid shaft) 412. The front-stage high-pressure stage power turbine 419 and the front-stage low-pressure stage power turbine 420 drive the front-stage low-pressure fan 411 via the front-stage fan drive shaft 412. The front fan drive shaft 412 passes through the inside of a connecting shaft 433 described later coaxially.
2) The front fan bearing 414 and the front fan bearing seal 415 of the front fan drive shaft 412 are fixed by the front fan fixing washer 416 and the front fan fixing bolt 417 through the front fan bearing fixing case 418.
3) A front fan front end cap 413 is attached to the front end of the front low pressure fan 411.
4) The front-stage high-pressure stage power turbine 419 and the front-stage low-pressure stage power turbine 420 are fixed to the front-stage power turbine bearing 421 and the front-stage power turbine bearing seal 422 by the front-stage power turbine bearing fixing nut 423 via the front-stage power turbine bearing fixing case 424. .
5) The front-stage low-pressure fan 411 is connected to the front-stage high-pressure stage power turbine 419, the front-stage low-pressure stage power turbine 420 and the front-stage fan drive shaft 412, and is driven by the front-stage high-pressure stage power turbine 419 and the front-stage low-pressure stage power turbine 420. The rotation direction of the first-stage low-pressure fan 411 is forward rotation (for example, right rotation).
6) The front stage power turbine tail cone 425 is attached to the rear end of the front stage low pressure stage power turbine 420.

(Rear fan section 430)
1) The rear-stage low-pressure fan 431, the rear-stage intermediate-pressure fan 432, and the rear-stage power turbine 438 are coupled by a rear-stage fan drive shaft (connection shaft) 433. The rear power turbine 438 drives the rear low pressure fan 431 and the rear intermediate pressure fan 432 via the rear fan drive shaft 433. Inside the rear fan drive shaft 433, the above-mentioned front fan drive shaft 412 penetrates coaxially.
2) The rear fan bearing 435 and the rear fan bearing seal 436 are fixed by the rear fan fixing nut 434 via the rear fan bearing fixing case 437.
3) The rear power turbine shaft 439 and the rear power turbine bearing seal 440 are fixed to the rear power turbine 438 by the rear power turbine bearing fixing nut 441 through the rear fan bearing fixing case 437.
4) The rear-stage low-pressure fan 431 and the rear-stage intermediate-pressure fan 432 are driven by the rear-stage power turbine 438, and the rotation direction is reverse (for example, left rotation).

(Fan case 450)
The front-stage low-pressure fan 411, the rear-stage low-pressure fan 431, and the rear-stage intermediate-pressure fan 432 are guided by a fan case 450 in order to guide the front-stage low-pressure fan 411 of the front-stage fan unit 410, the rear-stage low-pressure fan 431, and the rear-stage intermediate-pressure fan 432. Covered.

(Rear casing part 460)
1) A bypass flow mixing guide 462 is disposed in the rear casing 461, and the wind flow generated by the front-stage low-pressure fan 411, the rear-stage low-pressure fan 431, and the rear-stage intermediate pressure fan 432 is merged with the exhaust gas by the bypass flow mixing guide 462.
2) A total jet throttle duct 463 is disposed behind the rear casing 461, and the combined working fluid is throttled by the total jet throttle duct 463 to generate a total thrust. The flow velocity of the jet is increased by the restriction of all the jet restrictors duct 463 and taken out to the outside of the engine as thrust.
If the throttle is large, the core engine may be damaged by the pressure of the combustion gas generated by reheat. For this reason, it is necessary to vary the amount of aperture in the fighter afterburner. Since the combustion gas of the fighter afterburner is used as the total thrust, it must be variable.
In the present embodiment, unlike the fighter aircraft, the afterburner uses the entire amount of combustion gas to drive the front-stage high-pressure stage power turbine 419 and the front-stage low-pressure stage power turbine 420. For this reason, since a strong thrust can be produced, even if fuel is added again, the arrival time of the aircraft can be shortened, and cost effectiveness can be enhanced. The exhaust gas after driving the power turbine can be partially used as thrust. In order to convert the exhaust gas flow at the outlets of the front-stage high-pressure stage power turbine 419 and the front-stage low-pressure stage power turbine 420 into thrust, it is performed by throttling the entire jet throttle duct 463.
When the afterburner is not in operation, the exhaust gas after passing through the rear power turbine 438 driven by the rear-stage low-pressure fan 431 and the rear-stage intermediate-pressure fan 432 by the combustion gas generated by the core engine, the front-stage high-pressure power turbine 419 and the front-stage low-pressure power The turbine 420 is driven and discharged as exhaust gas to the atmosphere.

(Engine main case 470)
The wind flow generated by the front-stage low-pressure fan 411, the rear-stage low-pressure fan 431, and the rear-stage intermediate pressure fan 432 disposed at the front end of the engine passes through the passage inside the engine main case 470 and the outside of the core engine, and merges with the exhaust gas flow through the bypass flow mixing guide 462. And it becomes engine thrust and works outside. Here, the target bypass ratio of the present application for all engine thrusts is expected to be 3rd to 4th.

  The configuration of the turbine engine 400 according to the present embodiment has been described above. Hereinafter, the operation of the turbine engine 400 will be described with reference to FIGS. 8 and 9. As shown in FIG. 8, the combustion gas generated by being combusted in the combustor 118 rotates through the gas generation turbine 116-1 and is exhausted. As shown in FIG. 9, the exhausted combustion gas is sent to the rear power turbine 438 and rotates the rear power turbine 438. The rotation of the rear-stage power turbine 438 drives the rear-stage low-pressure fan 431 and the rear-stage intermediate-pressure fan 432 via the rear-stage fan drive shaft 433.

  The post-stage power turbine 438 is rotated, and the exhausted combustion gas is re-combusted by adding fuel again in the re-combustor 213 (see FIG. 5), and re-combustion gas is generated. The recombustion gas is sent to the front-stage high-pressure stage power turbine 419, rotates the front-stage high-pressure stage power turbine 419, and discharges the combustion gas. The exhausted combustion gas is sent to the front-stage low-pressure stage power turbine 420, rotates the front-stage low-pressure stage power turbine 420, and the exhaust gas is released to the atmosphere. The rotation of the front-stage high-pressure stage power turbine 419 and the front-stage low-pressure stage power turbine 420 drives the front-stage fan via the front-stage fan drive shaft 412. Further, the exhaust gas discharged from the front-stage low-pressure stage power turbine 420 still has energy, is throttled by the bypass flow mixing guide 462, becomes jet thrust, and is used as thrust (of the aircraft).

  The combustion gas that has been squeezed by the bypass flow mixing guide 462 and turned into jet thrust becomes a fan wind generated by the front fan unit 410 and the rear fan unit 430, and is squeezed by the entire jet throttle duct 463 to be an air flow thrust. Further, the combustion gas that has been squeezed by the bypass flow mixing guide 462 and becomes jet thrust is merged by the total jet squeeze duct 467, and all thrust generated in the turbine engine 400 is taken out.

  In the turbine engine 400 having the structure of the counter-rotating turbo fan configured as described above, the core engine unit including the gas generating compressor turbine unit 110 and the air turbine unit 130 has a guide cylinder 116 unique to the present embodiment. -3. Further, the turbine engine 400 has a rear-stage fan drive shaft 433 that connects a rear-stage low-pressure fan 431 and a rear-stage intermediate-pressure fan 432 and a rear-stage power turbine 438 that drives the rear-stage low-pressure fan 431 and the rear-stage intermediate pressure fan 432 as a hollow shaft. A solid front stage fan drive shaft 412 that connects a front stage low pressure fan 411, a front stage high pressure stage power turbine 419 that drives the front stage low pressure fan 411, and a front stage low pressure stage power turbine 420 is passed through the fan drive shaft 433 so as to pass through the front stage. The low-pressure fan 411, the rear-stage low-pressure fan 431, and the rear-stage intermediate-pressure fan 432 are arranged coaxially, and each set is rotated in the opposite direction.

(Effect of the fourth embodiment)
As described above, according to the present embodiment, the front-stage front-stage low-pressure fan 411, the rear-stage rear-stage low-pressure fan 431, and the rear-stage intermediate-pressure fan 432 are arranged coaxially, and the respective groups are rotated in opposite directions. The following advantages are obtained.
1) Since the downstream deflection of the upstream low pressure fan 411, the downstream low pressure fan 431, and the downstream intermediate pressure fan 432 is canceled by a combination of forward and reverse rotation, the counter torque applied to the engine body can be canceled.
2) With one set of fans, the energy that becomes a loss as a twist of the flow is eliminated by the cancellation, so that the thrust generation efficiency is improved.

  Moreover, the weight of the engine can be greatly reduced by eliminating the need for a transmission and a counter-rotating mechanism. Also, the separation of the core engine portion and the counter-reversing mechanism by the guide cylinder 116-3 and the combination of the counter-rotating structure that does not rely on mechanical coupling can reduce the accuracy of the center of rotation of each rotating shaft. Both significant reduction and high reliability can be achieved.

  As mentioned above, although preferred embodiment of this invention was described referring an accompanying drawing, it cannot be overemphasized that this invention is not limited to this example. It will be apparent to those skilled in the art that various changes and modifications can be made within the scope of the claims, and these are naturally within the technical scope of the present invention. Understood.

  For example, in the above-described embodiment, the suction negative pressure of the compressor is used to discharge the air turbine air, but the present invention is not necessarily limited to this example. You may exhaust the air of an air turbine by methods other than the suction negative pressure of a compressor being utilized.

  In the above-described embodiment, the variable guide vane device that adjusts the distribution of the amount of working air that drives the air turbine and the amount of combustion air supplied to the compressor by the angle area according to the vane opening angle is provided. However, the present invention is not necessarily limited to this example. The distribution of the working air amount and the combustion air amount may be adjusted by a method other than providing the variable guide vane device.

  In the above embodiment, the motor generator unit is installed between the compressor turbine shaft that supports the compressor and the guide cylinder that supports the gas generation turbine that drives the compressor. Is not necessarily limited to this example. The motor generator section may be provided at a position other than between the compressor turbine shaft and the guide tube.

  Moreover, in the said embodiment, although the inlet temperature of the air turbine was raised by collection | recovery of the exhaust heat of the exhaust gas discharged | emitted by the power turbine, this invention is not necessarily limited to this example. You may make it raise the inlet temperature of an air turbine by methods other than collection | recovery of exhaust heat of the exhaust gas discharged | emitted by the power turbine.

  Moreover, in the said embodiment, it adds the fuel to the exhaust gas discharged | emitted from the power turbine, burns, and it has the working air heating part which produces | generates combustion gas, and an air turbine is the combustion gas produced | generated by the working air heating part. However, the present invention is not necessarily limited to this example. The output shaft may be energized by a method other than rotating the air turbine with the combustion gas generated by the working air heating unit.

  Moreover, in the said embodiment, although the air compressed with the compressor with the combustion gas from a working air heating part was heated and supplied to the air turbine, this invention is not necessarily limited to this example. The air supplied to the air turbine may be heated by a method other than heating the air compressed by the compressor with the combustion gas from the working air heating unit.

  Moreover, in the said embodiment, although the combustion gas produced | generated by the working air heating part was supplied to the inlet_port | entrance of a combustor, this invention is not necessarily limited to this example. The combustion gas supplied to the inlet of the combustor may be generated by a method other than that generated by the working air heating unit.

  Moreover, in the said embodiment, the two-phase flow nozzle connected with an output shaft, and the two-phase flow nozzle which heats a medium with the combustion gas from a working air heating part, and isolate | separates the heated medium into a liquid phase and a gaseous phase The two-phase turbine is rotated by the liquid phase and the output shaft is urged. However, the present invention is not necessarily limited to this example. The output shaft may be energized by a method other than rotating the two-phase flow turbine.

  Moreover, in the said embodiment, it was arrange | positioned between the outlet of an air turbine, and the suction inlet of a compressor, and was equipped with the condenser which condenses a liquid phase and a gaseous phase, and the condenser was cooled with the air which passes. However, the present invention is not necessarily limited to this example. The condenser may be cooled by methods other than passing air.

The present invention includes the following inventions.
<Invention 1>
In a turbine engine that discharges by turning a power turbine with combustion gas generated by burning air compressed by a compressor in a combustor,
The power turbine is connected to an air turbine at an output shaft;
The turbine engine is rotated by compressed air heated by exhaust gas from the power turbine and urges the output shaft.
<Invention 2>
A working air heating unit for adding fuel to the exhaust gas discharged from the power turbine and burning it to generate combustion gas;
The turbine engine according to <Invention 1>, wherein the air turbine rotates by compressed air heated by the combustion gas generated by the working air heating unit and urges the output shaft.

  The above embodiment, application examples, and modification examples can be implemented in any combination.

100, 200, 300, 400 Turbine engine 110 Gas generating compressor turbine section (core engine section)
112 Compressor 112-1 Air compressor 112-2 Compressor air inlet 112-3 Compressed air bleed port 112-4 Compressor air outlet 112-5 Compressor casing 114 Compressor turbine 114-1 Compressor turbine shaft 114-2 Compressor turbine bearing 114-3 Compressor turbine bearing seal 114-4 Compressor turbine bearing fixing nut 116 Turbine 116-1 Gas generating turbine 116-2 Gas generating turbine casing 116-3 Guide cylinder 118 Combustor 118-1 Combustor main body 118-2 Combustor liner 118-3 Combustor air inlet 118-4 Combustor combustion gas outlet 118-5 Combustor casing 118-6 Fuel valve 120 Power turbine section 121 Output shaft 122 Output bearing 123 Output bearing seal 124 Output bearing fixed Nut 125 High pressure stage power Turbine 126 Low-pressure stage power turbine 127 Power turbine casing 128 Power turbine combustion gas outlet 130 Air turbine section 131 Air turbine 132 Turbine air inlet 133 Variable guide vane device 134 Turbine air outlet 135 Air turbine casing 136 Air heater 137 Heater air inlet 138 Heater air outlet 139 Heater casing 140 Power turbine outlet cone 141 Pipe between compressor bleed port / heater inlet 142 Pipe between heater outlet / air turbine inlet 143 Combustion gas exhaust port 150 Motor generator section 151 Motor generator rotation Child 152 Motor generator stator 210 Working air heating unit 211 Pilot burner 212 Flame holder 213 Reheat combustor 214 Reheat combustor casing 215 Reheat heat exchanger 216 Fuel Gas exhaust port 217 Compressed air extraction port 310 Working medium heating unit 311 Medium heater 312 Heater medium inlet 313 Heater medium outlet 314 Medium heater casing 315 Combustion gas exhaust port 316 Medium heater outlet / two-phase flow nozzle inlet piping 320 Two-phase flow nozzle section 321 Two-phase flow nozzle 322 Nozzle medium inlet 323 Nozzle medium outlet 330 Two-phase flow turbine section 331 Two-phase flow turbine 332 Turbine medium inlet 333 Turbine medium outlet 334 Two-phase flow turbine casing 335 Turbine casing seal 336 Two Phase flow nozzle outlet / two-phase flow turbine inlet piping 337 Turbine shut-off valve 338 Turbine regulating valve 340 Working medium condenser 341 Medium condenser 342 Condenser medium inlet 343 Condenser medium outlet 344 Medium tank 345 Two-phase flow turbine outlet / Clump Condenser inlet piping 346 Condenser outlet / media tank inlet piping 350 Media pump section 351 Media pump 352 Pump media inlet 353 Pump media outlet 354 Media tank outlet / media pump inlet piping 355 Media pump outlet / media heater inlet Piping 356 Pump / turbine bearing 357 Pump / turbine bearing seal 410 Pre-stage fan section 411 Pre-stage low-pressure fan 412 Pre-stage fan drive shaft (solid shaft)
413 Pre-stage fan tip cap 414 Pre-stage fan bearing 415 Pre-stage fan bearing seal 416 Pre-stage fan fixing washer 417 Pre-stage fan fixing bolt 418 Pre-stage fan bearing fixing case 419 Pre-stage high-pressure stage power turbine 420 Pre-stage low-pressure stage power turbine 421 Pre-stage power turbine bearing 422 Pre-stage power Turbine bearing seal 423 Pre-stage power turbine bearing fixing nut 424 Pre-stage power turbine bearing fixing case 425 Pre-stage power turbine tail cone 430 Rear-stage fan part 431 Rear-stage low-pressure fan 432 Rear-stage intermediate-pressure fan 433 Rear-stage fan drive shaft (connection shaft)
434 Rear stage fan fixing nut 435 Rear stage fan bearing 436 Rear stage fan bearing seal 437 Rear stage fan bearing fixing case 438 Rear stage power turbine 439 Rear stage power turbine shaft 440 Rear stage power turbine bearing seal 441 Rear stage power turbine bearing fixing nut 450 Fan case 460 Rear casing part 461 Rear casing 462 Bypass flow mixing guide 463 Total jet throttle duct 470 Engine main case

Claims (12)

In a turbine engine that discharges by turning a power turbine with combustion gas generated by burning air compressed by a compressor in a combustor,
A compressor turbine shaft that drives the compressor and the power turbine that extracts output is connected to the air turbine at the output shaft;
The air turbine heats the compressed air partially extracted during the compression by the compressor with the exhaust of the power turbine, and is driven by the high-temperature and high-pressure air to energize the output shaft. Characteristic turbine engine.   The turbine engine according to claim 1, wherein a suction negative pressure of the compressor is used to discharge air of the air turbine.   A variable guide vane device that adjusts the distribution of the amount of working air that drives the air turbine and the amount of combustion air that is supplied to the compressor by an angle area according to a vane opening angle is provided. The turbine engine according to claim 1 or 2.   The motor generator section is installed between a compressor turbine shaft that supports the compressor and a guide cylinder that supports a gas generation turbine that drives the compressor. The turbine engine according to any one of the above.   The turbine engine according to any one of claims 1 to 4, wherein an inlet temperature of the air turbine is increased by collecting exhaust heat of exhaust gas discharged from the power turbine. A combustion air is added to the exhaust gas discharged from the power turbine and burned, and the combustion air is generated, and the working air heating unit that heats the working air of the air turbine is provided.
The turbine engine according to any one of claims 1 to 4, wherein the air turbine rotates with compressed air heated by the working air heating unit and urges the output shaft.   The turbine engine according to claim 6, wherein the air compressed by the compressor is heated by combustion gas from the working air heating unit and is supplied to the air turbine.   The turbine engine according to claim 6 or 7, wherein the exhaust gas discharged from the power turbine is supplied to an inlet of the combustor. A two-phase turbine connected to the output shaft;
A two-phase flow nozzle that heats the medium with combustion gas from the working air heating unit and separates the heated medium into a liquid phase and a gas phase;
With
The turbine engine according to any one of claims 6 to 8, wherein the output shaft is energized by rotating the two-phase turbine in the liquid phase. A condenser arranged between the outlet of the air turbine and the suction port of the compressor, and condensing the liquid phase and the gas phase;
The turbine engine according to claim 9, wherein the condenser is cooled by passing air. A gas generation turbine that drives the compressor; a compressor turbine shaft that connects the compressor; a guide tube that supports the compressor turbine shaft; and a counter rotating mechanism;
The guide tube isolates the compressor, the core engine unit including the combustor, and the counter rotating mechanism,
In the counter rotating mechanism, the connecting shaft that connects the rear power turbine to which the combustion gas generated in the core engine unit is supplied and the rear fan driven by the rear power turbine is a hollow shaft, and the inside of the connecting shaft A solid shaft that connects a front-stage power turbine to which the working gas from the rear-stage power turbine is supplied and a front-stage fan that is driven by the front-stage power turbine passes through coaxially, and the rear-stage power turbine and the front-stage power turbine The turbine engine according to any one of claims 1 to 4, wherein rotation directions are rotated in directions opposite to each other. The air flow at the outlet of the rear fan is taken out as thrust by a throttle duct that tapers as it goes downstream;
The entire amount of combustion gas generated by the afterburner is used in the front stage power turbine that drives the front stage fan, and the exhaust gas at the outlet of the front stage power turbine is taken out as thrust by a throttle duct that tapers toward the downstream. The turbine engine according to claim 11, wherein: