JP2002106358A - Hybrid turbine engine - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a turbine engine to rectify the thermal efficiency of a turbine engine where a conventional axial flow is a primary object and its low cost hybrid turbine engine. SOLUTION: A turbine rotor is provided with a radiation plate rotating means to exert pressure operation of expansion fluid on a rotary shaft in a direction paralleling a shaft rotation direction. A radial duct compression means formed at the inner surface of a casing is formed at its side. A turbine engine is stored in a casing constituted in a manner to be provided with a suction port, a bearing, a casing compression means, a compression chamber, a feed valve means, a combustion chamber means, a fuel feed means, an ignition means, a surplus heat means, an expansion port, an exhaust port, a communicating means, and a cam mechanism. An electromagnetic disc, at which electric operation is interposed, is fitted in a magnetic disc aligned with a given empty distance with the turbine engine and provided on an electrically-driven shaft. A power generating and electrically driven means is coupled to a one direction transmission clutch to constitute a hybrid turbine engine.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

[0001] The present invention relates to a hybrid turbine engine.

[0002]

2. Description of the Related Art A conventional turbine engine is an internal combustion engine that enables high-speed shaft rotation and also enables fluid propulsion, and its functionality is widely known. However, special productivity is required in the structure and production, and the price is unmatchedly high. While the internal combustion engine has the function of enabling high-speed shaft rotation, it is largely related to its axial-flow rotation structure and the fluid shape of the axial-flow turbine blades, leaving factors that lower the output shaft torque or combustion efficiency. . In addition, it is difficult to directly use the finely divided fuel, and the frequent and rapid acceleration / deceleration operation required for the internal combustion engine mainly for the transport machine is used to reduce the inertia energy generated at the time of deceleration. The number of hybrid turbine engines that can be converted and recovered is limited to date.

[0003]

Conventionally, a compression and combustion expansion mechanism of a turbine engine has mainly an axial flow mechanism comprising a reaction turbine blade on the shaft side and an impulse turbine blade on the casing side. Many turbine blades (blades) provided in the casing have a diagonal flow shape for converting the axial flow energy of the fluid into rotation. Therefore, in the process of converting the axial flow energy possessed by the fluid into the axial rotational force through the oblique flow turbine blade, a large energy conversion loss is generated, and as a result, the thermal efficiency of the consumed fuel is reduced. . The problem to be solved by the present invention is to improve the means for compressing the fluid and the means for expanding the combustion fluid in the turbine engine, to correct the thermal efficiency, to enable the use of powdered fuel, to be versatile, and to further increase the inertia output. It is an object of the present invention to provide a hybrid turbine engine capable of recovery and an inexpensive provision thereof.

[0004]

In order to solve the above-mentioned problems, the present invention provides a radiating plate which arranges a plurality of disks at intervals on an output shaft of a turbine engine and radially partitions the plurality of intervals. A radial turbine rotor (shaft rotation expansion means) is provided, which is provided with radiation plate rotating means for applying the expansion pressure of the combustion fluid in the shaft rotation direction, to correct the shaft rotation conversion efficiency of the expansion fluid, and to improve the radial turbine rotor. A ring-shaped radial duct compressing means which is provided on both side surfaces of the casing with predetermined clearances and is arranged in a circumferentially smooth and multistage manner, and is fitted smoothly and radially to a similar casing compressing means provided on the casing side to be housed. A radial turbine rotor having a pair of radial compression means and improving the compression efficiency of the fluid is configured.
Then, the radial turbine rotor that constitutes the intake port, bearing, casing compression means, supply port, compression chamber, supply valve means, combustion chamber means, fuel supply means, ignition means, residual heat means, expansion port, communication port means, exhaust port,
The turbine engine is configured by being housed in a casing configured to include a cam unit, a governor unit, and the like. In addition, the intake valve means provided in the present invention has a function of intermittently supplying the compressed fluid to the combustion chamber means, so that accurate combustion of the supplied fuel and further backfire from the combustion chamber, suction negative pressure of the combustion chamber can be achieved. It is responsible for the combustion of powder fuel. The radial annular duct compression means or radiating plate rotating means constituting the present invention has a small number of operating sliding parts and lacks elements that require friction, airtightness and lubrication in function, so that it is possible to use powder fuel. it can. Further, according to the present invention, a magnetic disk having an output shaft of a turbine engine penetrating the shaft is formed with multiple intervals, and a magnetic casing is provided with bearings on both sides thereof, and the magnetic casing is provided with an electric shaft and a coil is provided. An electric motor is constructed by forming an electromagnetic rotating body in which electromagnetic disks formed by arranging and forming electromagnets are arranged in a multiplex manner with an empty space, and the electromagnetic disks of the electromagnetic rotating body are fitted with a predetermined gap in the space provided in the magnetic casing. And an electric motor that also functions as a generator, and is connected via a one-way transmission clutch, so that an inexpensive hybrid turbine engine that corrects low thermal efficiency can be configured and provided.

[0005]

DESCRIPTION OF THE PREFERRED EMBODIMENTS The present invention is directed to a bearing, an intake port, a radial casing compression means, a supply port, a compression chamber, a supply valve means, a combustion chamber means, a fuel supply means, an ignition means, a residual heat means, an expansion port, and a communication. Port means, exhaust port,
The radiating plate rotating means includes a radiating plate having a rotating shaft provided on a casing of a turbine engine including a cam means and a governor means and having a plurality of disks arranged at intervals on the shaft and partitioning the spacing into a plurality of radially arranged disks. This is a turbine engine in which a radial turbine rotor (shaft circumferential rotation expansion means) to be formed is configured and housed in a casing. Further, a hybrid turbine engine is formed by connecting an electric motor having a one-way transmission clutch to the output shaft of the turbine engine and having both an electric motor and a generator.

[0006] A rotating shaft is provided, and disks are arranged around the shaft with a predetermined space therebetween and fixed at a right angle to the shaft to form a disk space partitioned on the shaft. It is preferable to change the space between the disks in the arrangement order. A radial plate is provided with a radial plate radially in the disk interval and the disk gap to divide into radial regions to form radial plate rotating means for converting the expansion pressure of the expansion fluid into rotation. The expansion gap for expanding the expansion fluid is provided on either the inner peripheral surface of the casing, the radiation plate, the outer peripheral portion of the radiation plate, or the inner peripheral surface of the casing and the outer peripheral portion of the radiation plate. Further, it is preferable to provide the region for preventing the backflow of the expansion fluid in the rotating direction on the inner peripheral surface of the casing, and it is preferable to provide the expansion gap on the inner peripheral surface of the casing. A shaft is provided with a radiating plate rotating means to form a turbine rotor, and a duct is radially connected to both side surfaces of the turbine rotor to form a ring-shaped continuous radiating duct which is formed in a ring shape smoothly from the core to the outer peripheral portion. A ring-shaped radiating duct compression means for transferring or compressing a fluid in the outer peripheral direction by its inclination and centrifugal force along with rotation by rotating the duct having an angle or an inclination angle with a plurality of ducts arranged and connected in a multi-stage arrangement with a predetermined interval. A radial turbine rotor is provided and formed.

Bearing, intake port, radial casing compression means, supply port, compression chamber, supply valve means, combustion chamber means, fuel supply means, ignition means, residual heat means, expansion port, communication port means, exhaust port, cam means The radial turbine rotor is disposed adjacent to the inner peripheral surface of the casing of the turbine engine, which is also provided with governor means, and is housed in a ring shape to constitute the turbine engine.

[0008] Adjacent to the inner peripheral surface of the casing, adjacent to the annular continuous radiation duct compression means provided on the side surface of the radial turbine rotor to be accommodated in the form of a wheel, and on both sides of the radial turbine rotor, The provided annular continuous radiation duct compression means is provided with the same type of annular continuous radiation duct compression means to form the casing compression means. The casing is provided with a pair of radial ring-shaped duct compression means, which is fitted in the casing compression means provided in the casing and which is adjacent to or adjacent to the annularly arranged radial duct compression means of the radial turbine rotor in a smooth and radial multi-stage manner.

The fluid compressed from the central portion of the radially connected radial duct compression means as the radial turbine rotor rotates is radially compressed by the inclination and centrifugal force of the radial duct, and further radially and smoothly fit together. The fluid is sequentially compressed by the annular continuous radial duct compression means of the casing compression means composed of multiple stages, and the compression is alternately repeated, so that the fluid is efficiently pressurized to the outer peripheral portion.

A compression chamber is provided with a supply port at a predetermined position in the casing. The fluid pressurized in the provided compression chamber is temporarily accommodated through the provided supply port to absorb the pressure pulsation and then flow to the supply valve means provided on the supply port to the combustion chamber means. Powder fuel may be supplied to the compression chamber.

A predetermined supply valve means is provided on the supply ports of the compression chamber and the combustion chamber means. The supply valve means is controlled by a cam, a cam mechanism constituted by a casing, and a governor mechanism in the supply amount and supply time. The main purpose of providing the supply valve means and intermittently adjusting the supply of the fluid to the combustion chamber means is to properly burn the combustion chamber means, prevent flashback, and prevent negative pressure.
In addition, it prevents delayed propagation of powder fuel.

A combustion chamber means is provided at a predetermined position of the casing adjacent to the compression chamber and the supply valve means. The combustion chamber means is provided with an expansion port or a supply valve means for expanding a combustion fluid in a radial partition region of a disk interval of the fuel supply means, the ignition means, the preheating means, and the radiating plate rotating means, and the fuel supply means, the ignition means or the supply valve is provided. The supply means and the timing are adjusted by a cam mechanism and a governor mechanism, and a combustion chamber means is provided.

[0013] The expansion port provided in the combustion chamber means is provided in the first row of the disk gap forming the radial plate rotating means of the radial turbine rotor, and the expansion fluid injection angle of the expansion port is maximally approximated to the rotational circumferential direction of the radial turbine rotor. Have an angle. Further, the position of the inflation port is provided in the rotation direction front or near the front of the backflow prevention area on the inner surface of the casing.

The fuel supply means which constitutes the combustion chamber means is not particularly limited in type and system. The fuel supply and stop are clearly performed as precise operations, and the supply timing can be adjusted by cam operation and governor operation. Means.
In the fuel igniting means, the same operation and operation as described above are not particularly limited as long as the type and system are limited. The same can be said for the supply valve means.

An expansion port is provided in each of the disk gaps for sequentially supplying and expanding the inflation fluid to the disk gaps after the first row disk gap of the radiating plate rotating means. The expansion ports are provided in the expansion backflow prevention areas provided on the inner surface of each casing. In the vicinity of the front in the rotation direction. The injection angle of the expansion fluid is approximated to the rotation direction. In addition, the expansion fluid is sequentially arranged in series with the radiating plate rotating means to be expanded or actuated. .

The communication port means has a function of connecting the exhaust port of the expansion fluid supplied to the first row of the disk rotating means of the radial plate rotating means provided in the radial turbine rotor to the next disk spacing, and the expansion port to the radial plate rotating means. Thereafter, in the same manner, the expansion fluid supplied from the combustion chamber means is similarly arranged in a disc interval, and the expansion fluid is sequentially expanded in series over the entire disc gap area of the radiating plate rotating means, and efficiently to the radiating plate of the radiating plate rotating means. A communication port means for acting and converting to a shaft rotational force is provided on the outer peripheral portion of the casing. The exhaust port at the end is treated as an exhaust port.

An intake valve means at a predetermined position between the shaft and the casing;
A cam means for operating the fuel supply means and the ignition means is provided. The content is not detailed.

Governor means for operating fuel supply means and ignition means are provided at predetermined positions of the shaft and the casing.
The content is not detailed.

An electric motor having both an electric function and a power generation function is:
A plurality of predetermined magnetic disks provided at a high density with a single magnet and provided around a predetermined through-opening of the electric shaft are formed. A magnetic casing is provided with bearings arranged in a plurality of cylinders having a predetermined clearance. The bearing is provided with an electric shaft, and a plurality of predetermined electromagnetic disks having a single coil electromagnet at a high density are formed. A magnetic disk of a magnetic casing is fitted at a predetermined gap to an empty space of an electromagnetic disk forming an electromagnetic rotating body by forming a plurality of cylindrical electromagnetic rotating bodies having a predetermined space, and an electromagnetic wave is formed at an empty space of the magnetic casing. The electric motor is constructed by storing the electromagnetic disks of the rotating body with a predetermined gap therebetween. An electric motor that also functions as a generator by causing the electromagnetic coil to function as a motor via electricity or by collecting electricity from the electromagnetic coil.

A one-way transmission clutch is provided between the output shaft of the turbine engine and the electric shaft of the electric motor to connect them. Further, the other shaft without the electric motor clutch is connected to the output shaft to constitute a hybrid turbine engine.

When the output of the turbine engine is insufficient, electric power is supplied to an electromagnetic coil provided in the electromagnetic rotating body of the electric motor, and the motor output is supplied to the output shaft. The inertial energy generated from the output shaft accompanying the output reduction control of the turbine engine is switched to a generator function, and the rotational energy of the output shaft is recovered as power from the electromagnetic coil of the electromagnetic rotating body. When the load supplied to the output shaft is light, the one-way transmission clutch is slid, the output of the turbine engine is reduced to the idling state, and the motor is switched to the motor output state for supplying power to the electromagnetic coil of the motor.

In the hybrid turbine engine of the present invention, a radiation plate for efficiently rotating the shaft in the axial rotation direction is provided in the disk gap to constitute radiation plate rotation means, and further, both side surfaces of the rotor forming the radiation plate rotation means To provide a radial turbine rotor with a radial ring-shaped radiation duct, and housed in a casing equipped with similar compression means, thereby constituting a turbine engine capable of effectively correcting compression efficiency and expansion efficiency. . In addition, by forming both magnetic bodies to be formed in a disk shape, the distance from the axis of the volume to be occupied to the outer periphery is increased, the moment of the axial torque is increased, and the surface area of the magnetic field possessed by the desk-shaped magnet form is increased. A hybrid turbine engine having a function.

[0024]

Embodiments will be described with reference to the drawings.
1 and 2 show the overall structure of a hybrid turbine engine according to the present invention, wherein A1 is a front view of the turbine engine, A2 is a side view of the turbine engine, A3 is a front view of power generation and a motor, A
Reference numeral 4 denotes a one-way transmission clutch, and A5 denotes an output shaft. The hybrid turbine engine according to the present embodiment includes a one-way transmission clutch (A) for an electric motor (A3) having both functions of a turbine engine (A1) and an electric motor or a generator.
4) A hybrid turbine engine configured to be combined with and configured as described in 4). FIG. 3 shows the structure of the radial turbine rotor, in which a disk (2) is arranged on a shaft (1), a radiation plate (3) and a cylindrical or adjusting plate (10) are provided, and an expansion turbine means (A) is mounted on the shaft (1). 1) A turbine rotor is formed on the periphery, and further, annular radial duct compression means (B) is provided on both side surfaces of the turbine rotor with an empty space (6).
And a radial turbine rotor (C) is arranged in multiple stages in the outer circumferential direction. FIG. 4 shows a casing (S) which houses the constructed radial turbine rotor (C) and constitutes a turbine engine, and FIG. 5 shows a structure of the turbine engine. FIG. 6 is a configuration diagram of the radial duct compression means. A bearing (F) is provided in the casing (S) measuring section, a fluid intake port (E) is provided in the vicinity thereof, the shaft (1) is supported, and a radial turbine rotor (C) is provided in the casing (S). It is installed next to the casing (S). Casing (S) to be stored or radial turbine rotor (C) to be stored
Of the radial turbine rotor (C) and an expansion gap (5) for the fluid formed in the region between the radiation plate (3) forming the radiation plate rotating means (A) and the casing inner peripheral surface (T). ), The intake port (E), the shaft circumference in the vicinity thereof, the axis of the annular radial duct compression means (B) provided on both sides of the radial turbine rotor (C), the casing compression means (G constituting the casing (S)). ), Except for the supply port (H) and the surface adjacent to the backflow prevention region (8) of the expansion fluid provided on the inner peripheral surface (T) of the casing. Radial ducts (4) on both inner surfaces of casing (S)
Is formed in the shape of a ring, and is provided with an empty space (6) adjacent to the ring-shaped radial duct compression means (B) formed on both sides of the radial turbine rotor (C) to be housed and fitted smoothly. Casing compression means (G) is formed by arranging in multiple stages in the circumferential direction. A similar and similar ring-shaped radial duct compression means (B) provided on both sides of the radial turbine rotor (C) is disposed adjacent to the casing compression means (G), and is fitted radially and smoothly to a pair of radial duct compression means (D). ). FIG. 4 shows a pair of radial duct compression means (D) which are formed by fitting the casing compression means (G) and the annular radial duct compression means (B) provided in the radial turbine rotor (C) in a smooth and radial manner. It is a block diagram. With the rotation of the radial turbine rotor (C), the fluid introduced from the intake port (E) cools the bearing (F) and is introduced from the center of the radial duct compression means (D) near the shaft, and is arranged in multiple stages and smoothly with the rotation. The fluid is pressurized radially alternately through the annular radiating duct compression means (B) to be provided, and the supply port (from the last part of the annular radiating duct compression means (B) of the radial turbine rotor (C) is provided to the casing (S). H) flows down and is introduced into the compression chamber (I). The compression chamber (I) is responsible for the vaporization of the fuel supplied from the fuel supply means (K) when provided, and further has a supply valve means (J) which makes the supply of the compressed fluid different from the conventional turbine engine.
Absorbs the pulsation fluctuation of the pressure generated from the intermittent supply of the compressed fluid using, and stabilizes the supply of the compressed fluid to be supplied to the combustion chamber means (K). The compressed fluid supplied from the compression chamber (I) is supplied to the combustion chamber means (K) via the supply valve means (J). The supply valve means (J) supplies time-limited or intermittent supply of the compressed fluid to be supplied to the combustion chamber means (K).
Responsible for adjusting the supply amount, taking appropriate combustion in the combustion chamber means (K), flashback prevention, and negative pressure prevention measures. The fuel supply means (L) and the supply valve means (J) provided are a casing (S),
And cam means (U) arranged at a predetermined position on the shaft (1)
(Omitted on the drawing), and governor means (omitted on the drawing) (V). Fuel supply means (L) provided;
The formation and configuration of the supply valve means (J) are not particularly limited, and include means for operating accurately. A supply valve means (J) is provided adjacent to the combustion chamber means (K), and a fuel supply means (L), a residual heat means (N), and an ignition means (M) are combined to constitute a combustion chamber means (K). Let it. Further, an expansion port (P) for supplying the combustion fluid to the radiation plate rotating means (A) is provided so as to penetrate the casing (S) in the rotation direction front of the backflow prevention region (8) provided in the casing inner peripheral surface (T). The combustion expansion fluid supplied from the expansion port (P) provided in the casing inner peripheral surface (T) applies the expansion pressure to the radiation plate (3) of the radiation plate rotating means (A) provided in the radial turbine rotor (C). The radiating plate (3) is continuously rotated by the shaft (1) by inflating the expansion gap (5) provided on the inner peripheral surface (T) of the casing by causing it to act. The expansion fluid is the inner peripheral surface of the casing (T)
Is expanded through the expansion gap (5) provided in the above, and is discharged from an exhaust port (Q) provided through the casing (S) near the back in the rotation direction of the backflow prevention region (8). The expansion fluid discharged from the exhaust port (Q) penetrating through the casing (S) passes through the communication port means (R) provided on the outer periphery of the casing (S) to the expansion port (R) to the next radiation plate rotating means (A). P), and a radiation plate (3) of radiation plate rotating means (A) similarly constituting the next radial turbine rotor (C) from an expansion port (P) provided through the casing (S).
Is rotated through the shaft (1), and is discharged from the exhaust port (Q) provided in the same manner, and similarly, the fluid is expanded through the communication port means (R) to the next radiating plate rotating means (A). The expansion fluid supplied from the expansion port (P) provided in the combustion chamber means (K) is provided in the expansion port (P) provided in the entire radial plate rotating means (A) provided in the radial turbine rotor (C). A communication port means (R) for communicating the exhaust port (Q) with each of them is sequentially passed through, and the radiating plate (3) of the radiating plate rotating means (A) provided for each is sequentially rotated with the shaft so that the final exhaust port (R) is rotated. Exhaust from Q). A backflow prevention region (8) is provided on the inner peripheral surface (T) of each casing at a distance between the expansion port (P) and the exhaust port (Q) provided for each, and an expansion fluid to be supplied to the expansion port (P) is provided. By rotating the radiating plate (3) in the same rotational direction without backflow, the expansion can be continued until the expansion pressure owned by the radiating plate is finally reduced, and the radiating plate (3) can be rotated by the shaft (1). As described above, the fluid is compressed with high efficiency and the supplied fuel is combusted cyclically so as to effectively utilize the calorific value, and the expansion energy of the obtained fluid is converted into a shaft (1) rotational direction and multiple stages. Therefore, by configuring a structure capable of obtaining a strong and effective shaft (1) torque, the low thermal efficiency of the turbine engine can be corrected. A predetermined magnetic disk (Y) having a shaft penetrating portion is formed on a disk (Y) in which a single magnet is arranged and formed at a high density, and the magnetic disks are multiplexed with a predetermined clearance (11). The cylindrical magnetic casing (W) is provided with bearings (12) on both sides thereof, and the bearing (12) supports the electric shaft (13). Clearance intervals (11) of multiple magnetic disks (Y) array constituting magnetic casing (W)
In addition, an electromagnetic disk (Z) formed with a single coil magnet at a high density is provided at a predetermined gap (1) at a predetermined space (11).
The electromagnetic rotating body (X) is formed by fixing the electric shaft (13) supported by the bearing (F) by arranging and arranging 4). The electromagnetic casing (W) accommodates the electromagnetic rotating body (X), and electricity is interposed in the coil electromagnets forming the electromagnetic rotating body (X), thereby configuring the electric motor (A3) having both the electric motor and the generator. Means for interposing electricity in the electromagnetic rotating body is not particularly limited. The electric motor (A3) has a motor-driven shaft (13) provided with a one-way transmission clutch (A4) and coupled to the turbine engine shaft (1).
One of 3) is connected to the output shaft (A5) to constitute a hybrid turbine engine. When the output of the turbine engine is insufficient, electricity is supplied to the coil electromagnet of the electric motor (A3), and when the electric motor (A3) alone is output, the rotation speed of the turbine engine (A1) is kept in an idling state. A hybrid turbine engine that recovers generated inertial energy from the coil demagnetizing motor (A3) as generated power is configured, and a power system with high thermal efficiency is also configured.

[0022]

The present invention is embodied in the form described above and has the following effects.

By correcting the compression mode and the expansion means in the turbine engine, a Durbin engine excellent in combustion efficiency can be provided. In addition, an inexpensive, highly versatile and versatile turbine engine with high shaft torque and its hybrid turbine engine can be provided.

[0028]

[Brief description of the drawings]

FIG. 1 is an overall view of a hybrid turbine engine.

FIG. 2 is a configuration diagram of a hybrid turbine engine.

FIG. 3 is a configuration diagram of a radial turbine rotor.

FIG. 4 is a schematic view of a casing.

FIG. 5 is a configuration diagram of a turbine engine.

FIG. 6 shows radial duct compression means.

[Explanation of symbols]

 Reference Signs List A radiation plate rotating means B annular radiation duct compression means C radial turbine rotor D radial duct compression means E intake port F bearing G casing compression means H supply port I compression chamber J supply valve means K combustion chamber means L fuel supply means M ignition means N Preheating means P Expansion port Q Exhaust port R Communication port means S Casing T Casing inner peripheral surface U Cam means (omitted in drawing) V Governor means (omitted in drawing) W Electromagnetic casing X Electromagnetic rotor Y Magnetic disk Z Electromagnetic disk 1 Rotary shaft 2 Disk 3 Radiating plate 4 Annular continuous radiating duct 5 Expansion gap 6 Clearance gap 7 Expansion opening 8 Backflow prevention area 9 Cylindrical or adjusting plate 10 Magnetic disk 11 Predetermined clearance 12 Bearing 13 Electric shaft 14 Predetermined clearance 15 Output shaft

Claims (28)

[Claims] 1. A plurality of predetermined disks centered on the axis of a rotating shaft provided at predetermined intervals are arranged at a right angle in the axial direction, and a predetermined gap or axial peripheral region is formed at the disk interval. A plurality of radially dividing radial plates are provided, radially dividing a disk gap or a shaft peripheral region into a plurality of radially extending regions, and a radial plate rotating means for applying pressure of a combustion fluid expanding from the combustion chamber means to the radial plate to change the rotation to the axial rotation. A predetermined annular annular radiating duct is provided on both side disk end surfaces of the turbine rotor with a predetermined clearance and is arranged in a circumferentially smooth and multistage manner, and the fluid flows from the central portion to the peripheral direction with the rotation of the turbine rotor. A radial turbine rotor configured to include a ring-shaped continuous radiation duct compression means for compressing an intake port, a bearing, a casing compression means, a supply port, a compression chamber, A turbine engine configured to be housed in a casing including supply valve means, combustion chamber means, fuel supply means, ignition means, residual heat means, communication port means, exhaust ports, and expansion ports. 2. The radial turbine rotor according to claim 1, wherein the direction or the angle of the radial plate partitioning a predetermined interval of the disks into a plurality of radial spaces and the annular continuous radial ducts provided on both side surfaces is perpendicular to the axial rotation direction. 2. The turbine engine according to claim 1, wherein the radial turbine rotor is configured to have an inclination angle or a parabolic angle or a curved angle. 3. The radial circumference of the radial turbine rotor according to claim 1, wherein a predetermined gap of a disk interval provided on the shaft is changed in the order of being provided on the shaft, or the area of the disk provided on the shaft is changed in the order provided, and the circumference of the shaft is changed. 3. The radial turbine rotor according to claim 1, wherein the volume of the region is sequentially changed to constitute the radial turbine rotor.
A turbine engine according to claim 1. 4. A predetermined expansion opening in the radial turbine rotor according to claim 1, wherein a combustion fluid to be expanded from the combustion chamber means is sequentially expanded in a rotational direction on a radiating plate which divides a predetermined interval of the disks into a plurality of radial spaces. The radial turbine rotor is constituted by comprising:
A turbine engine according to claim 1. 5. An outer peripheral portion of a radial plate that radially partitions a predetermined gap or an axial peripheral region in the casing according to claim 1 and the radial turbine rotor accommodated in the casing, and an inner peripheral surface of the casing adjacent to the radial plate when the casing is accommodated. The radial turbine rotor or the casing is formed by providing a predetermined expansion gap for sequentially expanding the combustion fluid in the rotational direction in the area of the radial turbine rotor or the casing.
A turbine engine according to claim 1. 6. A predetermined expansion of the combustion fluid in the casing and the radial turbine rotor according to claim 1, wherein the combustion fluid is expanded in a rotating direction in an area adjacent to an outer peripheral portion of a radial plate and an inner peripheral surface of the casing of the radial turbine rotor housed in the casing. The turbine engine according to any one of claims 1, 2, 3, 4, and 5, wherein the casing and the radial turbine rotor are configured such that the expansion gap is formed by both the inner peripheral surface of the casing and the outer peripheral portion of the radiation plate. 7. A predetermined expansion gap for expanding a combustion fluid in a rotational direction in a region adjacent to an outer peripheral portion of a radial plate and an inner peripheral surface of a casing of a radial turbine rotor housed in the casing of the casing according to claim 1. The turbine engine according to any one of claims 1, 2, 3, 4, 5, and 6, wherein the casing is configured to be provided in an inner peripheral surface region of the casing. 8. The casing according to claim 1, wherein the expansion fluid is caused to act on the expansion gap formed between the inner peripheral surface of the casing and the outer peripheral portion of the radiation plate in the rotation direction of the radial turbine rotor, and the axial rotation direction of the expansion fluid. A casing comprising a predetermined backflow prevention region having no expansion gap of an expansion fluid for preventing backflow, provided in the rotation direction on the inner peripheral surface of the casing and behind the combustion chamber means expansion port.
The turbine engine according to any one of 3, 4, 5, 6, and 7. 9. A radial gap formed in the radial turbine rotor according to claim 1, wherein a radial gap is formed by a radial plate, and at least a conical area is formed. A radial turbine rotor comprising a cylinder or an adjusting plate parallel to an axis for adjusting a predetermined area or a predetermined volume in an outer peripheral direction to constitute a radial turbine rotor. The turbine engine as described. 10. Both inner surfaces of the casing adjacent to or adjacent to the annular continuous radial duct compression means provided on both side surfaces of the radial turbine rotor contained in the casing compression means constituting the casing according to claim 1. Rotation of the annular continuous radiation duct compression means provided on both side surfaces of the radial turbine rotor in which a predetermined annular continuous radiation duct is provided in a smooth and circumferential multi-stage with predetermined clearances to form and house casing compression means. Wherein the casing is provided with casing compression means for transferring or compressing the fluid in a radial direction along with the casing.
The turbine engine according to any one of 3, 4, 5, 6, 7, 8, and 9. 11. An inclined angle, a curved angle, or a parabolic angle included in a casing compression means constituting the casing according to claim 1, which is provided in a radiation duct constituting a ring-shaped continuous radiation duct compression means provided in a radial turbine rotor. Claims 1, 2, 3, wherein the casing is constructed by providing a contradictory or different inclination angle, curve angle, or parabolic angle in the annular continuous radiation duct of the casing compression means.
The turbine engine according to 4, 5, 6, 7, 8, 9, or 10. 12. The radial turbine rotor is housed next to or adjacent to the casing according to claim 1, and the annular continuous radial duct compression means provided on the radial turbine rotor is fitted to the casing compression means on the casing side. A pair of radial ring-shaped duct compression means to be constituted, a ring-shaped continuous radiation duct provided in both compression means and provided with a predetermined gap and provided in a smooth and circumferential multi-stage predetermined gap provided in both compression means 4. A structure comprising a pair of radial ring-shaped duct compression means configured to be fitted in a smooth and radial manner at intervals.
The turbine engine according to 4, 5, 6, 7, 8, 9, 10, 11. 13. A casing portion or a casing near a central portion of a ring-shaped radiating duct compression means provided at both sides of a radial turbine rotor housed in a casing at an intake port constituting the casing according to claim 1. The casing is provided with an intake port having a predetermined opening near or outside the two bearing portions to be formed, and the casing is constituted.
The turbine engine according to any one of claims 1 and 12. 14. The bearing according to claim 1, wherein the casing is provided with a predetermined bearing outside or in the vicinity of both intake ports or both ends of the intake port provided in the casing. Terms 1, 2, 3,
The turbine engine according to 4, 5, 6, 7, 8, 9, 10, 11, 12, or 13. 15. A fluid which is compressed is temporarily stored in a predetermined position on an outer peripheral portion of a casing in which a radial turbine rotor is housed adjacently in the compression chamber constituting the casing according to claim 1, and absorbs pressure pulsation. One or more compression chambers each having a predetermined volume are provided. The radial turbine rotor is accommodated in the casing. A compression chamber provided with a supply valve means or a supply port to a combustion chamber means provided with one or a plurality of supply ports to the combustion chamber means, and configured in a casing. 6, 7, 8, 9, 10, 1
The turbine engine according to any one of claims 1, 12, 13, and 14. 16. The compression chamber constituting the casing according to claim 1, wherein the compression chamber is formed by providing a fuel supply means, and the casing is configured to constitute the casing. , 7, 8, 9, 10, 11, 1
The turbine engine according to 2, 13, 14, or 15. 17. A supply valve means constituting the casing according to claim 1, wherein the supply valve means is provided on a supply port of a compression chamber provided on an outer peripheral portion of the casing, on a supply port close to the combustion chamber means, or to the combustion chamber means. 4. A casing comprising a single or a plurality of supply valve means for adjusting a supply timing and a supply amount of a fluid supplied near an inlet, and comprising the casing. 9, 1
The turbine engine according to any one of claims 0, 11, 12, 13, 14, 15, and 16. 18. The supply valve means constituting the casing according to claim 1, wherein the combustion chamber means is provided with the supply valve means to form the combustion chamber means to constitute the casing. 3, 4, 5, 6, 7, 8, 9, 10, 1
The turbine engine according to any one of claims 1, 12, 13, 14, 15, and 16. 19. A fuel supply means for supplying fuel, comprising one or more combustion chamber means having a predetermined volume at a predetermined position on an outer peripheral portion of the casing, wherein the fuel supply means comprises a combustion chamber means constituting the casing according to claim 1. An ignition port, a residual heat means, and an expansion port for expanding the combustion fluid to the radial plate rotating means of the radial turbine rotor are provided on the inner peripheral surface of the casing. 1, 2, 3, 4, 5, 6, 7, 8, 9101.
The turbine engine according to any one of claims 1, 12, 13, 14, 15, 16, 17, and 18. 20. Each of the disk gaps forming the radiation plate rotating means of the radial turbine rotor in the exhaust port of the casing according to claim 1, or the inner periphery of the casing adjacent to the radiation plate outer peripheral portion of the clearance. A casing provided with a predetermined exhaust port near each rear position in the rotation direction of each of the fluid backflow prevention areas provided on the surface;
2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12,
A turbine engine according to any one of claims 13, 14, 15, 16, 17, 18, and 19. 21. Each of the disk gaps forming the radiation plate rotating means of the radial turbine rotor in the expansion port constituting the casing according to claim 1, or the casing inner periphery adjacent to the radiation plate outer peripheral portion of the clearance. 10. A casing comprising a predetermined expansion port near each forward position in the rotational direction of each of the expansion fluid backflow prevention regions provided on the surface. , 10,
11, 12, 13, 14, 15, 16, 17, 18, 1
Turbine engine according to 9, 20 22. The communication port means constituting the casing according to claim 1, wherein the combustion fluid is sequentially expanded in each of the disc intervals provided with the radiation plates of the radiation plate rotating means provided in the radial turbine rotor, and the expansion pressure is radially reduced. A communication port means is provided on each of the exhaust ports which acts on the radiation plate of the turbine rotor to change the rotation and communicates with the expansion port in order, and a communication port for serially expanding the combustion fluid in each disk gap of the radiation plate rotation means of the radial turbine rotor for expansion. Claims 1 and 2, wherein the casing is constituted by means.
3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 1
3, 14, 15, 16, 17, 18, 19, 20, 21
Turbine engine described in 23. The rotary shaft and the casing according to claim 1, wherein the rotary shaft and the casing are provided at predetermined positions with cam means for operating supply valve means, fuel supply means, and ignition means. Claims 1 and 2,
2, 3, 4, 5, 6, 7, 8, 9, 10, 12, 13,
14, 15, 16, 17, 18, 19, 20, 21, 2
3. The turbine engine according to 2. 24. The rotary shaft and the casing according to claim 1, wherein the rotary shaft and the casing are provided at predetermined positions with governor means for operating supply valve means, fuel supply means, and ignition means, and the casing and the rotary shaft are constituted. Claims 1, 2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 1
2, 13, 14, 15, 16, 17, 18, 19, 2,
A turbine engine according to any one of claims 0, 21, 22, and 23. 25. The turbine engine according to claim 1, wherein powder fuel is supplied from an intake port or a fuel supply means constituting a casing.
6, 7, 8, 9, 10, 11, 12, 13, 14, 1
5, 16, 17, 18, 19, 20, 21, 22, 2,
25. The turbine engine according to 3, 24. 26. The turbine engine according to claim 1, wherein powder fuel or gas or liquid fuel is supplied from an intake port and fuel supply means constituting a casing. , 7, 8, 9, 10, 11, 1
2, 13, 14, 15, 16, 17, 18, 19, 2,
The turbine engine according to any one of claims 0, 21, 22, 23, 24, and 25. 27. A plurality of predetermined magnetic disks, each having a single magnet at a high density and having a through-opening of a predetermined electric shaft at its core, are arranged and formed in a multi-layered cylindrical shape having a predetermined space, and are formed at both ends thereof. A magnetic casing of a motor or a generator is formed with a predetermined bearing, and a plurality of predetermined electromagnetic disks having a high density of a single coil electromagnet on an electric shaft provided on the bearing are provided in a predetermined cylindrical shape with a predetermined interval. The electromagnetic disk of the magnetic rotating body is fitted into the empty space of the electromagnetic disk forming the electromagnetic rotating body with a predetermined gap, and the electromagnetic disk of the electromagnetic rotating body is inserted into the empty space of the magnetic casing with a predetermined gap. 27. A turbulent device according to claim 1, wherein said electric device has a motor or a generator by interposing electricity in an electromagnetic coil. A hybrid turbine engine configured to be coupled with a one-way transmission clutch on a rotating shaft of the engine. 28. The magnetic casing or the electromagnetic rotator according to claim 27, wherein both single magnets are alternately changed to constitute an electric means.
5, 6, 7, 8, 9, 10, 11, 12, 13, 14,
15, 16, 17, 18, 19, 20, 21, 22, 2,
27. The hybrid turbine engine according to 3, 24, 25, 26.