JPWO2015105202A1 - Thrust generator - Google Patents

Abstract

A thrust generating apparatus having an axial flow compressor according to the present invention is a moving blade of an axial flow compressor comprising a plurality of blade rows that are concentrically and alternately rotated in reverse. The blades that are inclined in the direction along the direction of the wind that is sent to each other can be installed, and the rotating shaft of the rotating blade that rotates in the reverse direction to the forward rotation is a rotating body for forward rotation with multiple rows of moving blades installed A rotating body that rotates alternately and reversely is provided with a plurality of rows of moving blades.

Description

  The present invention relates to a thrust generating device, and the thrust generating device of the present invention is manufactured as a heavy industry-related product only with the permission of the United States government and the Japanese government which is an ally of the United States in the country of the inventor. About what is possible.

In the present invention,
In the rotating body of the axial flow compressor, each of the individual parts or individual parts constituting the part that sends the flow from the front to the rear by the rotation of the rotating body to power the fluid, or “blades”, or “Wings” or “rotor blades”, and in this specification, “blades” or “wings” or “rotor blades” are collectively referred to as “blades” and are described below.
Rotating part of an axial flow compressor constituting a rotating shaft or rotating wheel for mounting a plurality of the blades or blades or rotor blades described above, or for integrating a plurality of the blades or blades described above. As "disk" or "ring"
An axial flow compressor in which a blade or blade or rotor blade and a disk or ring are fixed or integrally structured is referred to as a “rotor” or “moving blade”.
(Pages 389, etc. of Non-Patent Document 4, and pages 72, etc. of Non-Patent Document 37, and pages 58 and 59, etc., and Non-Patent Document 40, and Non-Patent Document 41, etc.) (See page 174, etc., and pages 107-109 of Non-Patent Document 32)
In an axial flow compressor, the aforementioned moving blades rotate to send a flow from the front to the rear, and by passing the flow, the flow is adjusted and fixed to send the flow backward with pressure. “Blade” or “wing” is referred to as “stator vane” or “stator vane”. In this specification, “stator vane” or “stator vane” is collectively referred to as “stator vane” as described below. And
For the rotating body configured as the rotating blade described above, a plurality of "static blades" are arranged radially around the rotation axis so as to be concentric, and the fixed portion is referred to as a "stator".
A cylindrical structure having a suction hole and an exhaust hole in the front-rear direction of the rotating shaft of the above-described rotating body, which supports internal components or is mounted with a stationary blade, is referred to as a “casing”.
Further, in a conventional gas turbine for an axial compressor, the compressor casing constitutes a “stator”, and the combustor casing comprises an outer cylinder casing and an inner cylinder liner inside the casing. Was equipped with a stationary blade called a "nozzle".
An axial flow compressor is a compressor in which air flows in parallel to a rotation axis, and is composed of rotor blades (rotary blades) on the rotating body side and vanes of stationary blades (fixed blades) on the engine body side (Non-Patent Document 38). (Pages 38 to 41, pages 102 to 106 and pages 112 to 116 of Non-Patent Document 40, pages 233 to 331 of Non-Patent Document 39, etc.).
A conventional axial compressor has a multistage structure in which a plurality of moving blade rows and stationary blade rows are alternately arranged in the axial direction, and usually a set of this moving blade row and stationary blade row is called a unit,
When the rotating body rotates, the flow of the working fluid is accelerated and sent from the front to the rear, and the kinetic energy obtained by the moving blade is converted into pressure when the working fluid is decelerated by the stationary blade.
That is, the conventional axial flow compressor includes a moving blade that sends a flow from the front to the rear as the rotating body having the blades rotates, and a suction hole and a suction hole in the front-rear direction of the rotation shaft of the axial flow compressor. This is a thrust generating device in which the stationary blades installed in the above-described casing for an axial compressor having an exhaust hole are stacked in multiple stages and combined so that air flows parallel to the rotating shaft.
(See Non-Patent Document 32, Non-Patent Document 36, Non-Patent Document 37, Non-Patent Document 38, Non-Patent Document 39, Non-Patent Document 40, and Non-Patent Document 41)
Ideally, the air flows along the blade surface of the compressor. However, when the air flow rate is small, the air does not flow along the blade surface and separation occurs. This decreases the air flow rate, increases the angle of attack of the blade, creates a separation zone on the back of the blade, causes a sudden pressure drop, and causes a stall phenomenon (stall).
In the compressor cascade, when the speed is reduced and compressed by turning the flow, a boundary layer is likely to occur and loss is likely to increase. To avoid loss, the blade angle should be adjusted to the air flow angle as much as possible. It will be necessary. (See page 289 of Non-Patent Document 39) That is, if the blade is too angled from the air flow (the angle of attack is too large), the flow is separated from the blade surface (page 203 of Non-Patent Document 34). , See page 86 of Non-Patent Document 35), which causes surging.
In order to prevent stalls, ordinary axial flow compressors are equipped with a device that extracts part of the air from the middle stage of the compressor, increasing the air flow rate through the compressor and reducing the angle of attack to prevent stalling. It was. Further, a guide vane at the compressor inlet of a method (variable vane) in which the vane of the compressor is variable (pages 138 and 140 of Non-Patent Document 38, etc.) and the vane angle is changed along the air flow. In addition, there are a method in which the angle of attack with respect to the moving blade is made appropriate by changing the mounting angle of the first several stages of the stationary blades, and a method of dividing into two axes, a high pressure shaft and a low pressure shaft. (See pages 56 and 57 of Non-Patent Document 38, pages 328 to 330 of Non-Patent Document 39)
A conventional moving blade (fan part, compression part, etc.) or stationary blade is made of metal or a composite material (see pages 112 to 116 of Non-Patent Document 40), and a conventional moving blade (fan). Part, compression part, etc.) is a blisk structure in which a blade part (described as a moving blade in Non-Patent Document 40) and a disk part (or a rotor part) are integrated, or a blade part and a disk part. There are various structures such as a dovetail structure separated from each other. The material, structure, shape, etc. of the moving blades and stationary blades used in the present invention are substances that have high corrosion resistance and high strength. The type is not limited. (Non-Patent Document 40, pages 112 to 116, Non-Patent Document 38, pages 52 and 56, etc.)
About the material of each conventional part in the gas turbine,
The low pressure compressor blade (fan part)
Titanium alloys (lightweight, high-strength materials that are resistant to corrosion and erosion) are mainly used, and metal-based composites of metals such as titanium alloys and silicon carbide fibers have been studied.
High pressure compressor
Titanium alloy, heat-resistant titanium alloy and nickel alloy (with creep resistance, high thermal conductivity, low thermal expansion coefficient, environmental resistance (corrosion resistance, oxidation resistance, etc.), etc. Use).
The vane of the low-pressure compressor is
Such as stainless steel and weldable titanium alloy,
The compressor disk
Such as stainless steel and titanium alloy
The liner of the combustor
Special superalloys with high nickel and chromium content (high strength, creep resistance, high thermal conductivity, low thermal expansion, oxidation resistance, etc.), etc.
The turbine blades and
Superalloys (those with high creep resistance, high breaking strength, high fatigue strength, high thermal conductivity, low thermal expansion, high temperature corrosion resistance, oxidation resistance, etc.), etc.
Turbine disc superalloy,
Casings Titanium alloys and nickel alloys for compressor casings, superalloys for combustor and turbine casings, fan casings using iron, titanium, aluminum and aramid fibers, epoxy resins and carbon fibers Using composite materials (hardness (hardness of deformation) and strength)
Various materials were used. (See Non-Patent Document 38, Non-Patent Document 39, and Non-Patent Document 40)
Also, gas turbine machining methods include precision casting, unidirectional solidification / single crystal casting, laser beam machining, electron beam machining, electrical discharge machining, chemical milling, electrolytic machining and coating.
(See Non-Patent Document 38, Non-Patent Document 39, and Non-Patent Document 40)
In gas turbines, in order to extend the life of parts due to the severe usage environment, corrosion resistant coatings are applied to compressors and turbines, heat resistant coatings are applied to turbines, and thermal barrier coatings using ceramics are applied to combustors and turbines.
(See Non-Patent Document 38, Non-Patent Document 39, and Non-Patent Document 40)
A composite material of epoxy resin reinforced with carbon fiber or boron fiber for fan blades, etc., using a metal cover on the front edge of the wing and using a three-dimensional fabric in the thickness direction of the blade, or material for high temperature parts In addition, new materials such as those using a metal matrix composite MMC, a ceramic matrix composite CMC, an intermetallic compound alloy, etc. are being developed.
Ceramic materials are silicon nitride and silicon carbide, and various technological innovations are still in progress.
In the description of the two-shaft engine in FIG. 3.12 on page 57 of Non-Patent Document 38, the description of the high-pressure shaft and the low-pressure shaft is interpreted as the opposite description in the present invention.
The bearing “Mechanical element that supports the rotating shaft and smoothly rotates the shaft” (see Non-Patent Document 4) is a rolling bearing “ball or roller is inserted between the outer ring and the inner ring to reduce the friction by rolling contact. Bearings. ”Sliding bearings“ Bearings where the bearing surface and the journal are in surface contact. ”(See Non-Patent Document 4), etc. There are rolling bearings mainly used for aviation, and molybdenum-based high-speed steel is used. The lubricating oil is forcibly supplied and lubricated and cooled (Non-Patent Document 38, pages 54 and 55, Non-Patent Document 39, pages 542 to 547, Non-Patent Document 30, Non-Patent Document 6, As long as the bearing used in the present invention satisfies the conditions of the present invention, the type, structure, material, and the like of the bearing are not limited.
Conventional gas turbine cooling devices include convection cooling, collision cooling, membrane cooling, and convection cooling, and the type and structure of the cooling device used in the present invention satisfy the conditions of the present invention. For example, the type is not limited. (See Non-Patent Document 38, Non-Patent Document 39, etc.)
An actuator is a conversion device that converts fluid energy of hydraulic oil into mechanical energy, and includes a hydraulic cylinder and a pneumatic cylinder that perform linear motion, and a hydraulic motor and a pneumatic motor that perform rotational motion. (Described on page 138 of Non-Patent Document 32)
“Guide” refers to “moving a machine part correctly in a certain direction using a slip pair” (see Non-Patent Document 4)
The mechanism refers to “a combination of parts that perform a certain relative movement when considering only transmission and conversion of machine movement” (see Non-Patent Document 4) and “the internal structure of the machine” (see Kojien 6th edition). Show
In the present invention, the guide mechanism is a machine structure in which machine parts such as rails are moved correctly in a certain direction using a slip pair.
FIG. 1 shows an example of a simplified diagram of a brief description of hydrodynamics, where FIG. 1A shows a blade (w) intended to generate a force component (L) perpendicular to the flow. FIG. 4 is a simplified cross-sectional view, wherein (Le) is a leading edge of a blade, (Te) is a trailing edge of the blade, a straight line connecting the leading edge and the trailing edge is a chord (ch), and a chord length is a chord length ( chL), the angle between the chord and the fluid flow direction (V) is the angle of attack (α), the upper surface of the blade is (wup), the lower surface of the blade is (wun), and the blade of the compressor has a length The shape is twisted in the direction. (Description is made with reference to page 85 of Non-Patent Document 35 and page 202 of Non-Patent Document 34)
FIG. 1 (B) shows an example of a simplified diagram of a blade placed in the flow. The blade (w), the region where the speed changes suddenly due to the viscosity of the fluid in the boundary layer (wL), and the main flow (ef) This shows the relationship between a region away from an object to a certain extent and not having a strong influence of viscosity. (Description is made with reference to page 211 of Non-Patent Document 34)
FIG. 1 (C) shows an example of a simplified illustration of delamination. Inside the boundary layer near the surface of the object (w), friction due to viscous force occurs according to the velocity gradient, and the kinetic energy of the fluid is The fluid is converted into thermal energy by the force, the fluid close to the surface of the object is decelerated, and the fluid particles having a low velocity in the vicinity of the object lose kinetic energy to flow downward and stop. At this time, since the pressure on the downstream side is high, a reverse flow is generated, and the streamline in the boundary layer from the upstream is peeled off from the surface of the object. This state is called separation, and the separation region is (se). (Description is made with reference to page 136 of Non-Patent Document 35 and page 211 of Non-Patent Document 34)
FIG. 1 (D) shows an example of a simplified diagram of a method for preventing separation, in which a new flow is blown into the boundary layer flow that is about to flow backward to make a flow with a large momentum.
(Description is made with reference to page 137 of Non-Patent Document 35 and page 212 of Non-Patent Document 34)
FIG. 1E shows an example of a simplified diagram of a method for preventing separation, in which a boundary layer flow that is about to flow backwards is sucked into a flow with a large momentum in the upper layer to be a surface flow of the object.
(Description is made with reference to page 137 of Non-Patent Document 35 and page 212 of Non-Patent Document 34)
FIG. 1 (F) shows an example of a simplified diagram of a method for preventing peeling, and a slot is provided by a front blade (fw) and a rear blade (rw) to accelerate fluid (page 212 of Non-Patent Document 34). And a plurality of blades such as a high-efficiency tandem cascade (explained with reference to page 116 of Non-Patent Document 40) due to a gap flow between the front blade (fw) and the rear blade (rw). There is something that uses.
FIG. 1G shows an example of a simplified illustration of a method for preventing peeling, and a small protrusion (explained with reference to page 137 of Non-Patent Document 35 and page 212 of Non-Patent Document 34) or a dent (Non-Patent Document). No. 33, page 80) is arranged on the surface of the object (w), and the boundary layer flow is made into a turbulent boundary layer and mixed with a flow having a large momentum of the upper layer to delay separation.
(H) of FIG. 1 shows an example of a simplified diagram of a method for preventing separation, and an eddy current generator is attached to promote mixing. (Description is made with reference to page 212 of Non-Patent Document 34)
FIG. 2A shows the blades of the front row of blades arranged in the circumferential direction of the rotating shaft and the rear rows arranged in the circumferential direction of the rotating shaft, which constitute the moving blade or stationary blade of the axial compressor. An example of a simplified diagram showing the blades of the blade row of
(W1) located in the front row is a blade in a row of moving blades or stationary blades arranged in the circumferential direction of the rotating shaft,
(W2) located in the rear row is a blade in a row of moving blades or stationary blades arranged in the circumferential direction of the rotating shaft,
(LX) is an axial reference line that is a line parallel to the rotation axis (hereinafter, in this specification, a line parallel to the rotation axis is referred to as an “axial reference line” or “a line parallel to the rotation axis”. To describe)
(Sa) is the angle formed by the chord line (ch) and the axial reference line (LX), the stagger angle,
In FIG. 2A, the angle of the stagger angle of the front row of blades (W1) and the angle of the stagger angle of the rear row of blades (W2) are "opposite direction" or "direction close to the opposite direction". It is configured.
(Explain with reference to Non-Patent Document 39)
In the example of the same or similar positional relationship between the blades of the front row of blades and the blades of the rear row of blades in FIG.
Positional relationship between moving blades and stationary blades constituting one stage of a conventional general axial compressor,
When the moving blades in the front row and the moving blades in the rear row are concentric and reversely rotated, the front blades rotate to flow gas from the front to the rear of the rotating shaft, There are some that allow gas to flow from the front to the rear of the rotating shaft as the rotor blades rotate.
FIG. 2B shows a conventional general axial compressor of a front row and a rear row of moving blades configured in a rotor, or a front row and a rear row of stationary blades formed in a stator. An example of a simplified diagram showing the positional relationship is shown. The stagger angle of the blade (W1) of the front row of blades arranged in the circumferential direction of the rotating shaft and the rear row arranged in the circumferential direction of the rotating shaft The stagger angle of the blade (W2) of the blade row is configured to be "parallel direction" or "direction close to the parallel direction".
In the example of the same or similar positional relationship between the blades in the front row and the rear row in FIG. 2B, the front stage fixed to the rotor of a conventional general axial compressor is used. And the following blades, and the positional relationship between the front and rear stator blades fixed to the stator.
(C) of FIG. 2 shows an example of a simplified diagram of a comparison between the front row of blades and the rear row of blades configured in the axial compressor,
A dotted line (xx ′) is an axial reference line (LX) that is a line parallel to the rotation axis of a moving blade that is positioned concentrically and rotates in the front-rear direction of the rotation axis.
The direction of the front row blades (w) and the rear row blades (w) of the axial compressor, that is, the front and rear direction of the rotating shaft and the front blade edge (Le) of the rotor blade, In the row of axial compressors (I, II, III, IV), in which the direction of Te) is the direction of the blades in the same direction as the direction of gas flow,
In the case of arrangements such as I and II, II and III, III and IV, and I and IV in the example of (A) of FIG. 2 and (C) of FIG. The direction of the blades in the front row of the compressor and the direction of the blades in the rear row are opposite directions,
In the case of the example of FIG. 2B or the example of the arrangement such as I and III or II and IV in FIG. 2C, in this specification, the blades in the row in front of the axial compressor The direction of the blades and the direction of the blades in the rear row were parallel.
FIG. 2D shows an example of a simplified diagram for explaining the axial flow compressor. When the moving blade (w) rotates in the direction of arrow 1, the upper surface of the blade (w) has a higher flow velocity than the lower surface. Therefore, the pressure on the lower surface is higher than that on the upper surface, and air flows in a direction parallel to the rotation axis of the arrow 2 (explained with reference to pages 100 to 101 of Non-Patent Document 32). The inclination of the blade (w) of the front row with respect to the line and the inclination of the blade (sw) of the rear row with respect to the axial reference line are “opposite directions”.
FIG. 2E shows an example of a simplified diagram of the air flow from the moving blades and the stationary blades. When the moving blade (w) rotates in the direction of the arrow 1, (Corresponding to C2 in FIG. 5.4 on page 240) and removing the swirl component of the gas flow exiting the moving blade with the stationary blade (sw) to remove the swirl component in the axial direction (direction parallel to the rotation axis (LX)) It has a role to shed.
In addition, as in a conventional general axial compressor moving blade and stationary blade, “the inclination of the blade (w) in the front row with respect to the axial reference line and the blade in the rear row with respect to the axial reference line ( If the inclination of w) is “opposite direction”, it is possible to remove the swirl component of the gas flow from the moving blade and flow it in the axial direction.
(Non-Patent Document 32, pages 120 and 197, Non-Patent Document 39, page 240, Figure 5.4, etc.)
2F is an example of a simplified diagram of a conventional general axial flow compressor, and FIG. 2G is an example of a simplified diagram of FIG. 2F viewed from a direction perpendicular to the rotation axis. (LX) is an axial reference line, and the front rotor blade (w1) and the rear rotor blade (w2) fixed to the same rotor (R) have the rotor (R) in the direction of arrow 1. By rotating, the gas is exhausted from the suction port toward the gas discharge port, and a flow is created in a direction parallel to the rotation axis of the arrow 4.
A conventional general axial compressor in which a plurality of rows of moving blades (W) fixed to the same rotor are arranged in multiple stages with a stationary blade (sw) interposed therebetween forms a stage. If the inclination of the moving blades (w) in the multi-stage row of the moving blades in the rear row and the moving blades in the rear row is not inclined in a parallel or substantially parallel direction, the flow of gas from the moving blades (w) It cannot flow in the axial direction (direction 4).
That is, in a normal axial compressor in which the rotor blades (w) that are concentric and multistage are attached to the same rotor (R), the inclination of the rotor blade that rotates behind is opposed to the inclination of the rotor blade of the previous stage. It is not possible to install blades with a typical inclination (that is, the inclination of a stationary blade with respect to a moving blade of a normal axial compressor).
FIG. 3A shows an example of a simplified diagram of a conventional turbofan engine (explained with reference to pages 155 to 175 of Non-Patent Document 39 and page 87 of Non-Patent Document 42). (1) Is a rotor of an axial flow compressor comprising a rotor and a turbine for fixing a rotating rotor blade for a fan, and (2) is a casing that surrounds and exhausts the rotor (1) of the axial flow compressor in a cylindrical shape, (3) is a bypass space constituted by a low-temperature bypass flow nozzle that does not pass through the high-pressure compressor but passes through the outer peripheral side, and (3 ′) is constituted by a high-temperature core flow nozzle that passes through the high-pressure compressor on the inner peripheral side. (4) is a combustor (including a combustion chamber) that burns fuel for rotating the turbine, (LX) is “a line parallel to the rotation axis”, and (LY) is “parallel to the rotation axis”. Half of an axial compressor that is a line perpendicular to the straight line Radial line "(hereinafter, a line perpendicular to a line parallel to the rotation axis is referred to as" radial line of the axial compressor "in the present specification). The low compressor, medium compressor and high compressor are collectively used as a compressor.
Regarding the combustor (4), the combustor is located between the compressor and the turbine, and is composed of an outer cylinder called a casing and an inner cylinder called a liner, and there are a can type, an annular can type, and an annular type (non-patent document). 38, pages 43 and 45, pages 105 and 116 to 118 of Non-Patent Document 40, pages 333 to 383 of Non-Patent Document 39, etc.), fuel injection Machine (explained with reference to page 51 of Non-Patent Document 38, etc.), in order to exceed the heat resistance temperature of the liner heated by combustion, cooling air is poured into the liner wall from the louvers and slits to protect the liner It has a structure to do.
(B) of FIG. 3 shows an example of a simplified diagram of a conventional turbofan engine, (1f) is a nose cone, (1r) is a tail cone,
The air from the low-pressure compressor (1Lr) is converted into a bypass flow from the space (3) created by the outer casing (2L) and the high-pressure side casing (2H) serving as a bypass flow nozzle, and the high-pressure compressor (1Hr). ) And a casing (2H) that surrounds the high-pressure compressor in a cylindrical shape, the core flow from the space side is mixed and exhausted from one nozzle,
The high pressure compressor (1Hr) is connected to the high pressure turbine (1Ht) via a shaft, and the low pressure compressor (1Lr) is connected to the low pressure turbine (1Lt) via a shaft.
(Description is made with reference to pages 100, 112, 125, 126, 135, 135, 136, and 169 of Non-Patent Document 40)
The turbine that drives the compressor by converting the high-temperature and high-pressure gas energy from the combustor into mechanical energy is the turbine, and the axial turbine is a stationary blade (nozzle) and moving blade (blade). ) Are arranged alternately (pages 46 to 49 of non-patent document 38, pages 106 to 108 and pages 118 to 120 of non-patent document 40, and non-patent document 39). Pp. 386 to 455).
In FIG. 3B, (af) is a reburning device, (af1) is a fuel injection strut, and (af2) is a flame holder, which mixes the combustion gas from the turbine and the air from the fan, It is an apparatus that reheats exhaust gas to obtain thrust, and consists of an outer cylinder and an inner cylinder, and is provided with louvers and slits for cooling.
(Pages 52 and 53 of Non-Patent Document 38, Pages 139 to 145 and Pages 342 and 343 of Non-Patent Document 39, Pages 117 to 121 of Non-Patent Document 36, (Non-Patent Document 40, page 100, pages 122-132, pages 120, 121, etc.)
A thrust deflection nozzle is provided on the exhaust side at the rear of the reheat device. The exhaust nozzle can be increased or decreased by a variable mechanism, and the thrust can be deflected from the axial direction to the direction perpendicular to the axis. There is also an axial thrust deflection nozzle. (Description is made with reference to page 121 of Non-Patent Document 40)
FIG. 3C shows an example of a simplified diagram of a conventional turbojet engine (explained with reference to page 86 of Non-Patent Document 42). Air from the compressor is sent to the combustor as it is to turn the turbine. A jet engine of the form.
Examples of the jet engine include a turboprop engine and a turboshaft engine (described with reference to pages 170 to 173 of Non-Patent Document 41).

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The conventional rotating shaft is coaxially or nearly coaxially arranged in the front-rear direction, and the rotor blade rows and stationary blade rows are alternately arranged, and the rotor blades constituting the rotating shaft rotate to rotate the air from the front to the rear. The axial flow compressor of the thrust generating device that was compressed and sent in the direction
In a rotor in which a row of blades of a moving blade inclined in a certain direction is installed, the direction opposite to the inclination of the blade (w) with respect to the axial reference line in front of or behind the row of blades of the rotor (conventional shaft) It was impossible to construct a row of blades arranged in the vane side of the vane side relative to the axial reference line of the flow compressor.
The conventional rotating shaft is coaxially or nearly coaxially arranged in the front-rear direction, and the rotor blade rows and stationary blade rows are alternately arranged, and the rotor blades constituting the rotating shaft rotate to rotate the air from the front to the rear. The axial flow compressor of the thrust generating device that was compressed and sent in the direction
There is an axial flow compressor that supports the rotation of the rotating shaft and transmits power to the blades of the rotor blades only on the rotation center side (shaft side) of the blade, and a portion that supports rotation of the rotating shaft and transmits power In an axial flow compressor that is only on the outer peripheral side of the blade of the moving blade,
In order to transmit power to the rotor blades, the rotor blades that are stacked in multiple stages alternately in the front-rear direction of the rotating shaft are separated separately, and with a simple structure and compactly rotated opposite to the forward rotating rotor blades. It was difficult to install a moving blade.
The present invention is to solve the problems of the conventional axial compressor as described above,
In the rotor blades of an axial flow compressor that constitutes a row of blades that rotate concentrically and alternately reversely,
The blades in the previous stage and the next subsequent stage can install blades that are inclined in the direction along the direction of the wind that is sent,
The rotating shaft of the rotor blade rotating in the reverse direction to the forward rotation is a rotating body for forward rotation in which blades for a plurality of blades are fixed, and a rotating body for reverse rotation in which blades for a plurality of rows of blades are fixed, The object is to be able to configure arbitrarily arbitrarily.

In order to achieve the above object, the solution for the axial flow type thrust generating device of the present invention comprises a moving blade having a row in which a plurality of blades with twists and angles are arranged, and a rotating rotating body. The rotating body for forward rotation and the rotating body for forward rotation as the rotating body for forward rotation and the rotating body for reverse rotation as the rotating body for reverse rotation, and the rotating body for reverse rotation described above. The center of rotation of the body is concentric or nearly concentric in the front-rear direction of the rotating shaft of the rotor blade, and is alternately combined to form multiple layers, and by rotating in each rotating direction, gas is supplied from the front to the rear of the rotating shaft. A rotary shaft that surrounds the vicinity of the outer periphery of the rotor for the axial flow compressor for exhausting gas in the direction from the front to the rear of the rotor for the axial flow compressor and the rotation shaft of the rotor for the axial flow compressor described above. Is a cylindrical hole structure penetrating in the front-rear direction, and the axial flow compression described above In an axial flow compressor comprising a casing for rotating and supporting a rotor for power, a plurality of blades arranged in a row on the inner circumference of the outer ring for power or the outer rotor for power A moving blade is configured by radially arranging and fixing in the inner direction of the ring or outer rotor for power, and a bearing structural unit for rotating and supporting the moving blade is configured on the outer peripheral side or inner peripheral side of the moving blade. The rotating body constituting the rotor power member on the outer peripheral side of the row of blades of the moving blades, and the plurality of blades arranged in a row on the outer circumference of the power disk or power inner rotor A rotating blade is configured by arranging and fixing radially outward of the disk for power or the inner rotor for power, and a bearing structural portion for rotating and supporting the moving blade is provided on the inner peripheral side or outer peripheral side of the moving blade. Configured, dynamic Rotating body constituting a power element for the rotor in the inner row of blades of, and characterized in that a configuration.
The axial flow type thrust generating device according to the present invention includes a rotating member moving in each row of moving blades composed of a plurality of blades constituting the moving blade of the rotor for the axial flow compressor described in 0049 above. A rotor for an axial flow compressor comprising a shroud or a connection ring for reinforcing connection between adjacent blades in a row of blades on a rotating circle located at the same or substantially the same distance from the rotation center of the blade, It is characterized by comprising.
The axial flow type thrust generating device of the present invention is the casing described in 0049 above, the outer peripheral side of the row of blades of the rotor blade in the rotor having the rotor outer ring or the rotor outer rotor described above. A structure part for the inner side of the casing, which is composed of a structure part for bearings for rotating and supporting the rotating blades and a structure part for bearings for rotating and supporting the rotating body. Features.
The axial flow type thrust generating device of the present invention is the casing described in the above 0049, on the inner peripheral side of a row of blades of a rotor blade in a rotor having an outer ring for a rotor or an outer rotor for a rotor. Rotation and rotation of the moving blades on the inner peripheral side of the blades of the moving blades in a rotating body having a rotor structure and a bearing structure for rotating and supporting the moving blades or a rotor disk or rotor inner rotor The structure of the bearing is a structure for the rotation of the bearing for support and the structure of the structure for the bearing for support. The structure portion of the casing is arranged and fixed radially on the circumference in the casing side direction.
The axial flow type thrust generating device according to the present invention is the rotor or magnet for the axial flow compressor described in the above-mentioned 0049 to 0052. The above-described rotor in the rotor for an axial compressor, and the stator structure corresponding to the above-described rotor, and the casing structure portion in the vicinity of the above-described rotor are configured. It is characterized by that.
The axial flow type thrust generating device according to the present invention includes a rotor for an axial flow compressor described in the above 0049 to 0052, and an outer ring for power of the rotor for an axial flow compressor in the structural part of the casing. Alternatively, a rotor for a rotor configured with gear teeth for power transmission on the circumference of the outer rotor for power and a gear device for transmitting power to the rotor for rotor described above are configured. The casing structure portion in the vicinity of the power outer ring or the power outer rotor is configured as described above.
The axial flow type thrust generating device according to the present invention comprises a rotor or a casing of an axial flow compressor described in the above 0049 to 0054, wherein a magnet or a magnetic body is configured as a component of a rotating body. A casing structure portion in the vicinity of the rotating body, wherein the conductor is configured for power, power generation, or braking by electric resistance corresponding to the rotating body and magnets or objects similar to the magnet of the rotating body. It is characterized by having a configuration.
The axial flow type thrust generating device of the present invention is the rotor for the axial flow compressor described in the above 0049, and the rotor constituting the rotor power member on the inner peripheral side of the row of blades of the moving blades, Alternatively, a gas turbine turbine for connection or integral configuration with a rotating body constituting the rotor power member on the outer peripheral side of the row of blades of the moving blade is configured.
The action of the above 0049 is a moving blade having a row in which a plurality of blades with twists and angles are arranged, and a rotating body rotating in either one of a rotating rotating body and a rotating counterclockwise rotation is ordered. The rotating body for rotation, the other rotating body as a rotating body for reverse rotation, and the rotational center of the rotating body for forward rotation and the rotating body for reverse rotation described above are concentric or substantially concentric in the longitudinal direction of the rotating shaft of the moving blade. Concentric, stacked in multiple layers, stacked in layers, and rotated in each direction of rotation, allowing gas to flow from the front to the rear of the rotating shaft, and for the axial flow compressor described above A cylindrical hole structure surrounding the outer periphery of the rotor for an axial compressor and penetrating in the front-rear direction of the rotating shaft for exhausting gas from the front to the rear of the rotating shaft of the rotor, and as described above A casing for rotating and supporting a rotor for an axial compressor, In the axial flow compressor, the plurality of blades arranged in a row on the inner circumference of the outer ring for power or the outer rotor for power are arranged radially inward of the outer ring for power or the outer rotor for power. And fixed to form a moving blade, and on the outer peripheral side of the row of blades of the moving blade, the structure for bearings is used for rotating and supporting the moving blade on the outer peripheral side or inner peripheral side of the moving blade. A rotating body constituting a rotor power member and a plurality of blades arranged in a row on the outer circumference of the power disk or power inner rotor radially toward the outer side of the power disk or power inner rotor An inner periphery of a row of blades of a rotor blade, which is configured by arranging and fixing to constitute a rotor blade, and a bearing structural part for rotating and supporting the rotor blade is formed on the inner peripheral side or outer peripheral side of the rotor blade. The rotor power member on the side. Therefore, the moving blades located in the rear row next to the front row of moving blades have blades inclined at an angle according to the direction of the wind sent from the front row of moving blades. It is possible to install in multiple stages a rotating body that rotates by the power from the rotating shaft side of the blade of the moving blade and a rotating blade that rotates in the reverse direction by the power from the outer peripheral side of the blade of the moving blade. It is.
The action of the above 0050 is the same as the rotation center of the rotor blades of the rotating body in each row of the rotor blades composed of a plurality of blades constituting the rotor blades of the rotor for the axial flow compressor described in the above 0049 or A rotor for an axial flow compressor having a shroud or a connection ring for reinforcing connection between adjacent blades in a row of blades on a rotating circle located at substantially the same distance. Therefore, it is possible to constitute a reinforcing support on the blades of the moving blades in the rotor for the rotor.
The action of the above 0051 is the rotation and support of the moving blade on the outer peripheral side of the row of blades of the moving blade in the rotor having the rotor outer ring or the rotor outer rotor described above in the casing described in the above 0049. The inner structure of the casing is composed of the inner structure of the casing and the structure of the bearing for rotating and supporting the rotating body and the structure for the bearing. It is possible to fix so that the rotary body which comprises a moving blade can rotate in the surface vicinity of the surface of this or a casing.
The operation of the above 0052 is for rotating and supporting the moving blades on the inner peripheral side of the blade row of the moving blades in the rotor having the outer ring for the rotor or the outer rotor for the rotor in the casing described in the above 0049. In a rotating body having a bearing structure or a rotor disk or rotor inner rotor, the bearing for rotating and supporting the rotor blade on the inner peripheral side of the blade array of the rotor blade A structure portion for rotating and supporting the rotating body with the structure portion, and a plurality of stationary blades or struts radially from the structure portion for the bearing that is not on the rotating body side described above in a radial direction in the casing side. Since the structure part of the casing arranged and fixed on the circumference is configured, the rotating body constituting the moving blade is fixed so as to be rotatable at the center side of the casing, that is, the rotation center side of the moving blade. Is possible
The operation of the above 0053 is the above-described rotor for an axial compressor and the structural part of the casing described in the above-mentioned 0049 to 0052. Since the rotor body in the rotor for an axial compressor and the conductor for the stator corresponding to the rotor described above are configured, the casing structure portion near the rotor is configured. On the outer peripheral side of the blade of the blade, it is possible to install a rotating body composed of a magnet or a magnetic body and a stator mechanism in a casing near the outer periphery of the rotor.
The operation of the above 0054 is the structure of the axial compressor rotor and casing described in the above-mentioned 0049 to 0052, and the outer ring for power or the outer rotor for power of the axial compressor rotor described above. The rotor for a rotor configured with gear teeth for power transmission on the circumference and the gear device for transmitting power to the rotor for the rotor described above are configured. Since the casing structure portion near the outer ring or the power outer rotor is configured, the axial flow type thrust generating device has an outer ring for a rotor having gear teeth, and its In the vicinity of the outer periphery of the outer ring for the rotor, it is possible to install a power mechanism comprising a power transmission gear for the outer ring for the rotor.
The operation of the above 0055 is the rotating body in which the magnet or the magnetic body is configured as a constituent part of the rotating body in the structure part of the rotor for the axial flow compressor and the casing described in the above 0049 to 0054, and the above-mentioned Because the structure of the casing structure near the rotating body described above, the conductor is configured for power, power generation, or braking by electrical resistance corresponding to the magnet of the rotating body or similar to the magnet. In addition, it is possible to install a generator or a device that reduces the rotational speed of the axial flow thrust generator by electric power on the rotating body and casing of the axial flow thrust generator.
The action of the above 0056 is the rotor for the axial flow compressor described in the above 0049, with the rotor constituting the rotor power member on the inner peripheral side of the row of blades of the rotor blade, or of the blade of the rotor blade Rotation that rotates with the power of the turbine because the turbine for the gas turbine for connection or integral configuration with the rotor constituting the rotor power member on the outer peripheral side of the row is constituted. It is possible to install a rotor for an axial flow compressor having a body in the configuration.

In the thrust generating apparatus of the present invention, blades positioned in the rear row next to the front row of moving blades can be installed with blades inclined at an angle in accordance with the direction of the wind sent from the front row of moving blades. Because it is possible to install the rotating body rotating by the power from the rotating shaft side of the blade of the moving blade and the moving blade rotating in the opposite direction by the power from the outer peripheral side of the blade of the moving blade, When installing an axial flow compressor with multiple stages of rotating blades rotating in the opposite direction behind the rotating blades rotating in one direction, multiple rows of moving blades rotating in the same direction can be efficiently It has the effect that it can be rotated by a rotating body.
The thrust generating apparatus according to the present invention can form a reinforcing support on the blades of the rotor blades in the rotor for the rotor, so that the rotation of the blades for the rotor blades in the rotor is rotated. This has the effect that a moving blade reinforced on both the center side and the casing side can be used.
The thrust generating device according to the present invention rotates in one direction because the rotor constituting the moving blade can be fixed so as to be rotatable on the inner surface of the casing or in the vicinity of the inner surface of the casing. When the moving blades that rotate in the opposite direction behind the moving blades are installed in multiple stages, there is an effect that the supporting portions for rotating the moving blades can be dispersed.
The thrust generating device according to the present invention can fix the rotating body constituting the moving blade to be rotatable at the center side of the casing, that is, the rotation center side of the moving blade. When the moving blades that rotate in the opposite direction behind the blades are installed in multiple stages, there is an effect that the support portion for rotating the moving blades can be concentrated on the rotation center side.
In the thrust generating device of the present invention, a rotor having a magnet or a magnetic body and a stator mechanism in a casing near the outer periphery of the rotor may be installed on the outer peripheral side of the blade of the rotor blade. Since it is possible, it has the effect that it can rotate a moving blade using electric power in the casing side of the rotating blade which carries out reverse rotation alternately.
The thrust generating device of the present invention is an axial-flow type thrust generating device comprising: a rotor outer ring having gear teeth; and a rotor outer ring in the vicinity of the outer periphery of the rotor outer ring. Since it is possible to install a power mechanism composed of a power transmission gear, even in the case of a normal jet engine compressor, the power of the turbine can be It has the effect that a moving blade can be rotated using.
In the thrust generating device of the present invention, a generator or a device that reduces the rotational speed of the axial thrust generator by electric power can be installed on the rotating body and casing of the axial thrust generator. Therefore, there is an effect that power can be generated by an axial compressor for power, or the rotational speed of the compressor can be adjusted using electric power.
The axial flow type thrust generating device of the present invention can be installed with a rotor for an axial flow compressor having a rotating body that rotates with the force of a turbine. This has the effect of being able to design a thrust generating device of the formula.

FIG. 1 is a simplified example of a simple description of hydrodynamics. FIG. 2 is an example of a simplified diagram for explaining an axial compressor. FIG. 3 is a simplified example of a conventional jet engine. FIG. 4 is a shaft of claim 1 of the present invention. FIG. 5 is an example of a simplified diagram of a compressor blade that can be used in the present invention. FIG. 6 is a simplified diagram for explaining a blade of claim 6 of the present invention. FIG. 7 is an example of a simplified diagram of a compressor blade of claims 1 and 5 of the present invention. FIG. 8 is an example of a simplified diagram of a compressor blade of claim 1 of the present invention. FIG. 9 is a diagram of a compressor blade of the present invention. FIG. 10 is a simplified example of a casing structure that can be used in the present invention. FIG. 11 is a simplified example of a hollow structure that can be used in the present invention. FIG. 14 is used in the present invention. An example of a simplified diagram of the structure of a possible box-shaped thrust generator 5 is an example of a simplified diagram of a hydraulic device that can be used in the present invention. FIG. 16 is an example of a simplified diagram of a deflecting plate that can be used in a thrust generating device. FIG. Example of simplified diagram

In the axial flow compressor of the present invention, in the forward rotating blades and the reverse rotating blades that are alternately combined in a plurality of rows,
When a set of a rotor blade having a forward rotation axis and a shaft having a next reverse rotation axis is used as one stage,
In addition, when a stationary blade is sandwiched between a rotating blade with a forward rotating shaft and a rotating blade with a reverse rotating shaft that are combined in multiple rows alternately, in front of the moving blade with the rotating shaft in the same direction. There is a case where a group up to a row of blades in one row is made one stage.
FIG. 4 shows an example of a simplified diagram of an axial flow compressor portion for explaining “axial flow compressor” according to claim 1 of the present invention,
(LX) is the “front-rear direction of the rotating shaft of the moving blade”, and FIG. 4A is the “rotating body rotating right and rotating body rotating left” according to claim 1. One of these is the “rotary body for forward rotation” and the other is the “rotary body for reverse rotation”, and the blades (W) of the front and rear blades with twists and angles are indicated by arrows. By rotating in the direction, the air is compressed from the front to the rear of the rotating shaft and exhausted.
The front row of moving blades sends the flow to the rear row of moving blades (the direction of (C2) described in FIG. 5.4 on page 240 of Non-Patent Document 39), but the rear row of blades is the direction of flow. It is a feature of the moving blade of the present invention that it can be tilted along the axis.
FIG. 4B shows an example of a configuration in which a stationary blade (sW) is interposed between a front row and a rear row of moving blades (W), and the flow from the moving blade (page 240 of Non-Patent Document 39). (Direction (C2) shown in FIG. 5.4) is sent in the direction of rotation from the front to the rear of the rotating shaft in alternating directions. In the present invention, the stationary blade (sW) behind the moving blade (W). Then, rectification is performed along the flow, and the moving blade (W) in the next row of the stationary blade (sW) is inclined in the same direction (parallel direction) with respect to the front and rear axes as the previous stationary blade (sW). Therefore, it becomes possible to perform rectification along the flow by the stationary blades and acceleration of the flow by the moving blades (the inclination angles themselves may be the same or different, and the manufacturer can arbitrarily To do).
In addition, as shown on pages 103 and 104 of Non-Patent Document 40, a row of inlet guide vanes is provided in front of the front row of moving blades of the present invention, or the moving blades are arranged according to the rotational speed of the moving blades. There are no limitations on the type of variable vane mechanism (also described on page 56 of Non-Patent Document 38, etc.) provided on the stationary vane so as to optimize the introduction angle.
FIG. 5 shows an example of a simplified diagram of an electric rotor blade that can be used in the present invention. FIG. 5A is a view of the air suction side of the electric rotor blade as seen from an oblique direction. 5 (B) is a view of FIG. 5 (A) as seen from the upper front, and FIG. 5 (5) is a rotating shaft or bearing for rotating the moving blade (if it is a protrusion, it becomes a shaft and has a hole shape). (6) is a blade of a moving blade for sending air backward, and (7) is a “power outer ring or power outer rotor” according to claim 1 of the present invention. The outer ring (7) for a rotor according to claim 5 of the present invention, wherein the outer ring (7) has a magnet (8) of a "rotor power member" on the outer periphery of the ring and the blade (6) is fixed on the inner periphery of the ring. The “stator for the rotor described above” according to claim 5 of the present invention is installed in a casing or a fan casing and rotated. (6) is the “twisted or angled blade” according to claim 1, and (5) is the “inner circumferential side of the blade” according to claim 1. The outer ring for power is composed of a “structure part for bearings for rotating and supporting the moving blades”.
FIG. 5 shows a type utilizing the operating principle of an in-wheel motor for an electric vehicle (refer to pages 54 to 57 of Non-Patent Document 17, etc.).
FIG. 6A shows an example of a simplified diagram for explaining the moving blade of claim 6 of the present invention, and FIG. 6A shows a “power outer ring or power similar to claim 6 that rotates in a certain direction. A rotor for an axial compressor with “tooth gear teeth for power transmission” (9 ′) installed on the outer circumference of the outer rotor for the rotor and blades for moving blades installed on the inner circumference. (10) is a "power outer ring or power outer rotor" that rotates in the reverse direction to (9), and (10 ') is "a gear tooth for power transmission". 10) rotates around a dotted line (X) which is the rotation center of the rotation shaft, and (9) and (10) are the counter-rotating “rows of blades” according to claim 1, respectively. If the rotating body constituting the rotor power member is installed on the inner peripheral side of the rotor, the moving blade of claim 6 can be obtained.
The gear (11) is connected to the casing or the engine structure in the vicinity of the casing so as to be rotatable,
The gear (11) rotates about the rotating shaft (12) that rotates about the dotted line (Y) of “the radial line of the axial compressor”,
Gear (11) is connected to (9 ') and (10') so that the gear teeth mesh,
The gear (11) rotates (9 ′) and (10 ′) in the opposite directions in the direction of the arrow shown in the simplified view of FIG. .
6C, a gear having an axis (X ′) parallel to the rotation center (X) of the rotating shaft is connected to the outer periphery of the outer ring for a moving blade similar to claim 6 of the present invention ( An example of a simplified diagram of the casing structure in the vicinity of the outer ring for power ") is shown, and the rotating shaft (14) having the rotation center (X ') connecting the gears (13) on both sides is rotated, whereby (13) (9 ') on both sides where the gear teeth mesh with each other rotate in the same direction.
FIG. 6D shows an example of a simplified diagram of the combination of FIG. 6A and FIG. 6C. The rotors 9 on both sides connected to the turbine shaft rotate to rotate the gear (11 ) In which the rotor (10) rotates in reverse, the left and right gears (13) are connected via a transmission (14 ″), and the transmission (14 ″) is usually Like the accessory gearbox (see page 165 and page 179 of Non-Patent Document 41) used in the jet engine and the like, it is provided outside the moving blade.
A portion where a reduction gear, a gear, or the like for changing the rotating speed of the moving blade is provided on the rotating shaft side of the moving blade (page 36 of non-patent document 41 and page 174 of non-patent document 39). ˜page 175), the type of the blade is not limited as long as it satisfies the conditions of the present invention, such as being installed on the outer circumferential side of the moving blade.
(13) and (14) make it possible to disperse the load of the moving blade connected to the turbine on both the rotor side and the outer peripheral side of the ring.
The power transmission device is described in Non-Patent Documents 14, 15, 16, 17, 18, 19, etc., and the type of the power transmission device is not limited as long as the claims of the present invention function safely. .
Further, the transmission (14 ″) includes a rotating shaft (14 ″) to a power transmission device of another rotor or an axial compressor, and transmits power to a portion requiring other power. As long as the claims of the present invention function safely, their types are not limited.
FIG. 7 shows a simplified diagram of an example of a model showing the positional relationship of the axial compressor according to claim 1 of the present invention, and bearings, cages and their supporting structures used in the claims of the present invention are: There are various types such as rolling bearings, plain bearings and bearings, structures and materials similar to those used in jet engines, and those using the bearing for alternator of Non-Patent Document 6, etc. Those types are not limited as long as they satisfy the requirements. (See pages 54 and 55 of Non-Patent Document 38, Non-Patent Documents 6 and 7)
FIG. 7A is a schematic cross-sectional view of an electric compressor rotation power mechanism for compressing air and sending it from the front to the rear, and FIG. 7A is a claim. 1. An axial flow compressor in which “the rotation centers of the forward rotation rotor and the reverse rotation rotor are concentric or substantially concentric in the front-rear direction of the rotating shaft of the rotor blade, and are alternately combined to form multiple layers” It is a moving blade.
The rotor of the power mechanism for rotation in the axial compressor of FIG. 7A includes “power disk or power inner rotor” (15) and “power outer ring or power outer rotor” (26). And
In the taper-shaped “power disk or power inner rotor” (15), a magnet (21) is installed in (15) as a rotor for a motor, and a conductor (electric wire) is provided as a stator for the motor. Installed coil part (20),
In the cylindrical “outer ring for power or outer rotor for power” (26), a magnet (29) is installed in (26) as a rotor for a motor, and a conductor is used for a function as a stator for a motor. The coil part (28) having the (electric wire) was installed in the “structure inside the casing” (23),
This is a power mechanism for rotating the compressor.
In (A) of claim 7,
"Power disk or power inner rotor" (15)
(15) Installed on the inner peripheral side of the moving blade: a bearing structure for rotating and supporting the moving blade (17F / 17R),
The "casing" (23) of claim 1 is fixed to "the casing" (23). Bearings (18F / 18R) provided in the “structure part for bearings” (22), fixed to “shi” (23F / 23R),
Is rotatably fixed via a bearing (19),
"Power outer ring or power outer rotor" (26)
(26) Installed on “the outer peripheral side of the rotor blade: a bearing structural portion for rotating and supporting the rotor blade” (17F ′ and 17R ′);
The "structure part for bearings" (18F 'and 18R') according to claim 3, which is installed in the "casing" (23) of claim 1.
Is rotatably fixed via a bearing (19),
A support structure including a bearing structure or a shaft structure for supporting the rotating body is used.
(A) of claim 7
The rotor blades rotating in one direction are arranged in a row on the outer circumference of the “power disc or power inner rotor” (15) according to claim 1, “arrayed and fixed radially outward”. It is a “rotary body” in which three rows of blades (16) for a plurality of blades are arranged,
The rotor blades rotating in the other opposite direction form a row on the inner circumference of the “power outer ring or power outer rotor” (26) according to claim 1, arranged radially in an inward direction. And “fixed” is a “rotary body” in which two rows of blades (27) for moving blades are arranged in two rows.
FIG. 7A shows the force of the magnet rotor (21) installed on the inner side of the “power disc or power inner rotor” (15) and the conductive coil (20) installed on the rotating shaft (22). The motor outer ring or power outer rotor (26) is installed on the outer side of the magnet rotor (29) and the casing (23) having a hole structure on the outer periphery of the electric rotor blade. Although it rotates with the force with "the stator conductor corresponding to the above-mentioned rotor", as long as the conditions of the present invention are satisfied, the shape, structure, and type of material are not limited.
In addition, it is installed in various places if technically possible, such as the types of bearings used in the present invention, such as rolling bearings, plain bearings and bearings, combinations of bearings, and the positions of the bearings on the outer ring for the rotor. These types are not limited as long as they satisfy the conditions of the claims of the present invention.
FIG. 7B is a simplified view of the moving blade fixing support portion installed in the air introduction passage, as viewed from the front in the vertical direction of FIG. 5. A plurality of stationary blades or struts are radially arranged on the circumference in the casing side direction from the bearing structural portion that is not on the rotating body side. The stationary vane-shaped legs (25) and (24), which are the “structure portion of the fixed casing”, are circumferential structures that fix the legs (25),
It can be installed in various places such as a combination of bearings used in the present invention, and a constituent position of a rotor outer ring (rotor), a rotor disk (rotor), a bearing, and the like. As long as the conditions are satisfied, there are no limitations on the fixing method, shape, structure, and material of the rotor and the rotatable rotor in the casing.
(C) of FIG. 7 is a model diagram simply showing the positional relationship between the ring-shaped inner side bearing blade fixing portion (15) and the shaft side bearing fixing portion (22). 22) is a cross-sectional view in which (17R) is positioned outside through a bearing (19), with a support leg (30) being fixed and a bearing retainer etc. are omitted. The shape, structure, material, and the like of the bearing and the cage are not limited as long as they satisfy the conditions of the present invention.
(D) of FIG. 7 is a simplified diagram of “power disk or power inner rotor” (15), which is a blade fixing portion of the inner-side moving blade, based on the compression portion of the jet engine (the jet engine is a blade Although the portion located at (27) is a simplified diagram of stationary blades), the types thereof are not limited as long as they satisfy the conditions of the present invention, such as the shape, structure, and material of blades and rotors of moving blades.
FIG. 7E shows an example of a simplified view of the moving blade portion of FIG. 7F viewed from a direction parallel to the rotation axis. A cylindrical “power outer ring or power outer rotor” (26 The blades (27) of a plurality of moving blades are radially arranged inside and fixed, and the rotating shaft ring is arranged on the rotating shaft side (the inner peripheral side of the moving blade) of the blades (27) of the plurality of moving blades. A ring (26 ′) that serves as a bearing for rotating the rotor blade for connection with (SWR) is fixed.
Further, when either (26) or (26 ′) in FIG. 7E is a shroud or a connection ring for reinforcing connection between adjacent blades, the rotor for an axial compressor according to claim 2 is provided.
FIG. 7 (F) is a simplified view of claim 1 of the present invention of the appearance of the blade fixing portion (15) of the moving blade and the stationary blade as seen from the direction perpendicular to the rotation axis of FIG. 7 (E). An example of
The rotating shaft ring (SWR) is made up of the stationary blades (SW) by the stationary blades (SW) fixedly installed inside the casing (23) and the plurality of radially arranged stationary blades (SW). ) And the rotating shaft side of the rotor blade (27) can be rotated on the outer peripheral side of the bearing ring (SWR) for supporting the rotor blade. The rotor disk (rotor) is connected to the rotating shaft of the rotating shaft (SWR) and the rotating blade (16) rotating in the reverse direction to the rotating blade (27) is fixed on the rotating shaft side of the rotating shaft ring (SWR). This shows an axial flow compressor having the configuration 15).
The thrust generating device having the shape shown in FIG. 7 (F) can be installed on the rotating shaft side because a moving blade fixed by a stationary blade can be installed from the rotating shaft side of the axial compressor. The rotor can transmit power of a rotating blade rotating in the opposite direction without receiving mechanical friction of the moving blade.
FIG. 8 is a simplified diagram of an example of a model showing the positional relationship between the “casing” (23) according to claim 4 of the present invention and the “compressor in which a plurality of moving blades are layered”. While compressing the air by having the rotation center coaxially or substantially coaxial in the direction and the blades for right rotation and the blades for left rotation (16) and (27) alternately rotate in reverse and combined in multiple stages It exhausts from the front to the rear of the casing.
FIG. 8A is a simplified cross-sectional view of the electric rotor blade from the side. FIG. 7A shows that the rotor outer ring (26) is fixed by the casing (23) and rotates. The rotor outer ring (32) is fixed by a ring-shaped bearing (31) so as to be rotatable by the inner rotor (15).
The power outer ring (32) in FIG. 8 is fixed to be rotatable by the bearing structure (31) through the inner rotor (15) and the bearing (19). As long as the conditions of the claims of the present invention are satisfied, such as the types, combinations, and configuration positions of the bearings and bearings, those types are not limited.
8A is rotated by the force of the magnet rotor (21) installed inside the rotating rotor (15) and the conductive coil (20) installed on the rotating shaft (22). The rotor (32) is rotated by the force of the magnet rotor (29) installed on the outside and the conductive coil (28) installed in the casing (23) having a hole structure on the outer periphery of the electric rotor blade, thereby compressing the air forward. Although it is an electric rotor blade having a structure that can be used in the power part of a brushless motor or an AC motor, the shape, structure, and type of material are not limited as long as the conditions of the present invention are satisfied.
FIG. 8B is a simplified view of the cross section of the dotted line (xx ′) of FIG. 8A viewed from the front, and shows a ring-shaped inner rotor bearing (15) and a shaft-side bearing. Although it is a model figure which showed the outer rotor (31) which fixed the positional relationship of a fixing | fixed part (22) and the blade | wing (27) which rotates reversely with an inner rotor (15), the bearing retainer etc. are abbreviate | omitted. However, the types of the shape, structure, and material of the bearing, bearing, and cage are not limited as long as they satisfy the conditions of the present invention.
FIG. 8C is a simplified view of the external appearance of the thrust generator of FIG. 4 in which the blade fixing portion (33) of the moving blade on the inner side has a rotor connected to the turbine. An outer rotor (31) is fixed to a stationary blade (34) having a rotation shaft so as to be rotatable in the front-rear direction, and an outer rotor (33) rotating in a reverse direction to (31) is connected to a turbine of a jet engine. The shape is not limited as long as it satisfies the conditions of the present invention, such as the shape, structure, and material of blades and rotors of a moving blade.
FIG. 9 shows an example of a simplified diagram showing the vicinity of a moving blade according to claim 1 of the present invention,
(IR) is defined in claim 1 as “a row outside the power disk or power inner rotor ... a radially arranged and fixed configuration of the moving blades”.
(OR) is defined in claim 1 as "a row outside the outer ring for power or outer rotor for power ... arranged radially and fixed to form a moving blade"
(SW) shows a stationary blade of a type used in a normal jet engine, etc.
(Ca) is a "cylindrical hole structure surrounding the outer periphery of the axial compressor rotor and penetrating in the front-rear direction of the rotating shaft, ..., casing".
FIG. 9A shows a compressor for a compressor, in which a pair of a rotor outer ring that rotates in a certain direction and a rotor outer ring that rotates in a reverse direction are layered in pairs.
(B) in FIG. 9 shows a rotor blade (IRf) that is located on the front side of a plurality of rotor outer rings (OR) that rotate in the reverse rotation direction, and a rear side (IRf). A single axial compressor is shown in which a moving blade (OR) and a stationary blade (SW) are sandwiched between moving blades (IRr), which are positioned (IR), rotating in a certain direction. Is.
FIG. 9C shows an example of a simplified view of a stationary blade as seen from the front. The ring structure on the inside keeps the support and atmospheric pressure in the vicinity of the rotor of the moving blade. There are no limitations on the type, such as a mechanism, shape or structure such as a combination of a shaft or a bearing structure using any bearing.
FIG. 9D shows a single rotor outer ring (OR) that rotates reversely to two stationary blades (SW) between one blade (IR).
FIG. 9E shows a rotor outer ring (OR) having two independent counter-rotating motions with respect to (IR) between one rotor blade (IR) and rotor blades (IR) and (OR). ) Are provided with stationary vanes (SW) on both front and rear sides.
In FIG. 9, the casing (Ca) has a space for ventilation from the vicinity of the intake port to the vicinity of the exhaust port having almost the same size, but actually the space for ventilation is partially squeezed. However, the shape and the type of structure are not limited.
The type of the outer ring is not limited, for example, the outer ring for the rotor having a power source on the center side is kept at a constant rotational speed, and a plurality of outer rings for the outer peripheral side having various rotational speeds are provided.
The number of blades in (IR) and (OR), the number of rotating rotor blades, the pattern of their combination, the shape, structure, and material constituting them are various, so long as they satisfy the conditions of the present invention. Those types are not limited.
(A), (B), (C), and (D) in FIG. 10 are casings that allow air to flow to the outer peripheral side of the moving blade that flows gas to the inner peripheral side of the moving blade that can be used in the present invention. The simplified view of an example of the passage part of the air of an outer rotor shape or an inner rotor shape is shown, (A) is the simplified view of the passage surface of the casing shape or the outer rotor shape of the exhaust port side narrowed, (B) FIG. 4B is a simplified diagram of a casing-shaped or outer rotor-shaped air passage surface that is gradually narrowed from the inlet side to the exhaust port side, and FIG. FIG. 4D is a simplified view of an inner rotor-shaped air passage surface, and FIG. 4D is a simplified view of an inner rotor-shaped air passage surface that is gradually widened between the intake side and the exhaust port side and the exhaust port side is widened. ,
There are no limitations on the type of device installed near the casing or casing, such as a bleeder, a stationary blade, or a variable stationary blade, or the shape, material, or structure of the casing, ring, disk, or rotor in the casing or rotor.
(E) in FIG. 10 is narrowed in the shape in which the intermediate portion is narrowed when assembling the casing or outer rotor in which the exhaust port side in (35) is gently narrowed and the inner rotor in (36). Although it shows what is assembled by sandwiching from both sides of the part, it may be of a shape that is divided into upper and lower parts and fixed by sandwiching the moving blades from above and below as in a normal casing (Non-Patent Document 40). (Page 103) The type is not limited.
Further, as described in Non-Patent Document 41, page 179 and the like, there are various types of compressor casings and fan casings (fan casings) of conventional thrust generating devices. There are various types of structures and materials, and the types are not limited as long as the conditions of the present invention are satisfied.
FIG. 10 (F) shows what is assembled by sandwiching the inner rotor (15) from both sides of the bearing of the outer rotor (31).
FIG. 10G shows an example in which the rotor member (38) is connected and fixed with bolts (37 and 37 ′) with threads.
FIG. 10 (H) shows an example of a simplified view of the rotor portion using FIG. 10 (G) as seen from the front, and FIG. 10 (38) shows an example in which a bolt (38) is fixed on the circumference. It is.
Each member may be produced by a 3D printer (see Non-Patent Document 27 and Non-Patent Document 26), a machine tool (see Non-Patent Document 28), a mold, or the like (page 21 of Non-Patent Document 26). Etc.) The type is not limited.
The types of production using a 3D printer are metal hot melt lamination (such as page 53 of Non-Patent Document 27), multi-layer lamination solidification (such as page 53 of Non-Patent Document 27), and binders, which are lamination production methods. Spray lamination (such as pages 67 and 71 of non-patent document 27), 3D sand casting (such as page 70 of non-patent document 27), directional energy deposition (such as page 77 of non-patent document 27) Or melt deposition (such as page 104 of Non-Patent Document 26), laser direct lamination (such as page 104 of Non-Patent Document 26), or electron beam melting (such as page 77 of Non-Patent Document 27). In addition, by a manufacturing method such as a powder sintering method (such as page 92 of Non-Patent Document 26) or thin film lamination (such as page 79 of Non-Patent Document 27), the shape or structure is complicated, or the interior is hollow. It becomes possible to make things like a grid.
In manufacturing using a machine tool, it is possible to cut into various shapes by simultaneous multi-axis control processing, and various types of processing using a lathe etc. depending on the parts, and the conditions of the claims of the present invention are satisfied. As long as they are satisfied, the types of the parts and members of the present invention are not limited, such as the method of manufacturing and processing.
FIG. 11 shows an example of a simplified diagram of a structural portion that can be used in the present invention. FIG. 11A is a rotating shaft with a hollow inside, and FIG. FIG. 11C is a cross-sectional view of A) viewed from the side. FIG. 11C is a stationary vane that can be used in the present invention, and FIG. 11D is a side view of FIG. A more complicated structure can be manufactured using a 3D printer, a machine tool, a mold, etc., and the structure used in the present invention should satisfy the conditions of the present invention. If it is, those types are not limited.
FIG. 12 shows an example of a simplified diagram of the structural parts that can be used in the present invention.
FIG. 12A shows a simplified diagram in which the rotor constituting magnet and the conductor of claim 5 are configured in FIG. 7F, and the stationary blade (SW) is fixed to the casing (23). The magnet (21) installed on the outer peripheral side of the rotating body (15) located on the rotation center side, the conductor (20) being installed on the rotation center side to constitute the "casing structure part" according to claim 5, It is the simple figure which showed what rotates with a conductor (20).
FIG. 12B shows a simplified view of FIG. 12A viewed from the side, and the moving blade “power outer ring” (26) of FIG. 7E between the front and rear (SW). It has a space where can be installed.
(C) of FIG. 12 shows a simplified view of a “casing structure portion” in which the stationary blade (SW) is fixed to the casing (23) and the conductor (20) is installed toward the outer peripheral side on the rotation center side. A rotor blade can be installed and rotated between the outer peripheral side (23) and the inner peripheral side (20).
(D) in FIG. 12 shows that a plurality of conductors (C) in FIG. 12 passing through the inside of the stationary blade (SW) are formed in the front-rear direction of the rotating shaft, and a row of blades is formed between the stationary blades (SW). 12 is a rotor for an axial flow compressor having a shape in which a rotor blade (15) having a bearing portion configured to constitute a power member of a rotor on the circumferential side and rotatably supported on the outer circumferential side of a row of blades is installed. Although (D) is different from the moving blade of the present invention, it can be used as a part of the moving blade of the present invention.
FIG. 13A shows a state in which one row of blades is formed on the inner side of the rotor (26) constituting the rotor power member on the outer peripheral side of the blade row of the rotor blades of claim 1. It is a simplified diagram.
(B) in FIG. 13 is installed on the outer peripheral side of (A) in FIG. 13, and the row of blades in (A) in FIG. 13 rotates on the intermediate rotating body in (15). FIG. 5 is a simplified diagram showing a blade array part and two blade rows in the front-rear direction that are connected to a component supporting a rotor blade made of a stationary blade on a rotating body of (15 ′).
FIG. 13C illustrates the rotor blade (26) of claim 1 and the stator (SW) of the stationary blade for fixing the rotor blade which is divided into the upper and lower portions in the same manner as the stator of a normal axial compressor. (15) is a structure of a bearing structure for rotating and supporting the moving blade on the outer peripheral side of the moving blade (15) by (SW), and (15) is a row of blades (16) of the moving blade. The power member for the rotor is configured on the inner peripheral side of the rotor.
FIG. 13D is a simplified diagram showing the member (38) and the bolt (37 ′) for fixing the members together.

FIG. 14 shows an example of a simplified diagram of the structure of a box-shaped thrust generating device that can be used in the present invention and has a compressor inside, and FIG. 14A can be used in the present invention. FIG. 14B is a cross-sectional view of a possible box-shaped structure for thrust generation from the side, FIG. 14B is a cross-sectional view of FIG. 14A viewed from above, and FIG. And (D) is a cross-sectional view of the rear structure of the box-shaped structure, FIG. 14 (E) is a cross-sectional view of the lower vicinity structure of the front portion of the box-shaped structure, and FIG. It is sectional drawing of the upper part vicinity structure of the front part in a box-shaped structure.
14A is a rotor blade having a rotor structure on the outer peripheral surface side, and FIG. 14A is a rotor blade of FIG. 5 that is connected to a rotating shaft 39 and rotates. The stator coil (41) provided inside (51) is rotated by the principle of a motor, and has a radial blade structure similar to a stationary blade of a jet engine via a rotating shaft (39) (51 ) Is connected to the leg (42) fixed to.
(45) and (51) constituted by a nacelle having a plurality of casings connected in the front-rear direction of the air flow inside the casing, and a ring-shaped rotating shaft (44) having a hollow center disposed in one casing And the above-mentioned ring guide bearing installed in the other casing and connected through the center side of the rotating shaft by the connecting portion (43) of the connecting ring having a hollow center, and rotated clockwise and counterclockwise And a casing structure having a ring-shaped rotating shaft mechanism in which a cavity is formed for ventilation.
(47) is an opening / closing lid that can cover part or all of the opening, and is a lid that opens and closes by vertical movement, and is a bypass that exhausts air from (42), (46) It is an axial flow compressor.
14 (B), (48) is a hole penetrating vertically inside the nacelle formed by (43) and (44), and (48 ') is the air passing through the compressor (46) to the outside. (45) is a simplified view of the vicinity of a box-shaped casing that can be rotated by a robot arm (52) connected to (51) by a rotating shaft.
(C) and (D) in FIG. 14 show that the lid of (47 ′) and (47 ″) rotates and (45) changes the flow of exhaust gas by blocking a part of the air exhaust port. This device is similar to a deflecting plate for direction change having a rotation axis at an angle perpendicular or oblique to the longitudinal line of the aircraft configured near the exhaust hole at the rear of the box-shaped nacelle. .
FIG. 14E shows an opening opening / closing lid (47 ′ ″) that can cover a part or all of the opening at the lower part of the opening of the air inlet of the nacelle (47 ′). The lid (47 ''''), which enters the inside of '') and changes the size of the lid, rotates and moves in the direction of the arrow, so that the opening of the air intake port is moved forward or backward. The opening / closing lid that can be opened and the box-shaped nacelle are connected and opened and closed.
14 (F) shows the vicinity of (47) of FIG. 14 (A), and (47) opens and closes the opening by rotating in the vertical direction in the direction of the arrow. Yes, (47) opens to form a bypass that can exhaust air.
FIG. 15 shows an example of a simplified diagram of a part of an aircraft fuselage structure that can be used in the present invention, and FIG. 15A shows the components and actuator mechanism of the aircraft as viewed from the direction of extension of the rotating shaft. FIG. 15 (B) shows a relationship diagram when FIG. 15 (A) is viewed from the direction perpendicular to the rotation axis, and the component member (57) of the aircraft is rotated by the rotation axis (58). Actuator (55) and actuator (56) are connected separately, (56) is a mechanism that is directly fixed to (55) and expands and contracts to change the angle of (55) and (57), and (55) expands and contracts As a result, (57) moves in the longitudinal direction of the aircraft.
15A and 15B use an actuator that reciprocates linearly, but the type is not limited, for example, an actuator that rotates such as a hydraulic motor is used in (58).
FIGS. 15C and 15D are simplified views of an example of an actuator that can be used in the present invention. The actuator is linearly moved by a cylinder 60 having a rod 59 therein. By reciprocating, the actuator expands and contracts, and the rotation shaft (61 ′) provided on the rod support portion (61) fixed to the rotation shaft (60 ′) provided on (60) and the rod support portion (59) rotates. It is an actuator which moves the angle and composition position of the thrust generator of the present invention.
(E) in FIG. 15 is a simplified view of the lower part of the nacelle, (62) is a thrust generating device of the present invention having an air inlet, and (62 ′) is a rotation connected to the upper nacelle. It is a ring for.
FIG. 15F shows an example of a simplified diagram of the vicinity of the rear part of the aircraft according to the present invention, in which a through hole from the upper surface to the lower surface of the rear part of the aircraft of (63) is provided in the vicinity of the horizontal tail of (64). is there.
FIG. 15G shows a simplified view of an example of a lid that can cover the opening of the suction port of the thrust generating device provided in the lower portion of the thrust generating device, and the nacelle (62) as viewed from the front-rear direction of the aircraft. The lid (65) that covers the opening in the left and right double-side opening is shown in the lower part of the door and opens and closes in the direction of the arrow. The actuator for the double opening of the door (65) is either a rotary movement or a sliding movement. It may be a thing and those types are not limited.
15 (H) and FIG. 15 (I) are simplified views showing an example of a guide mechanism for sliding the structural members of the aircraft installed in the vicinity of the inside of the aircraft in the front-rear direction, and (H) has a rail structure. 2 is a cross-sectional view of the slide guide mechanism as viewed from the front-rear direction of the aircraft, and FIG.
(66) is a connecting portion with the actuator mechanism, and is an example in which the wheel of (67) moves the guide rail of (68) in the direction of the arrow.
FIG. 16A shows an example of a simplified view of the deflecting plate that can be used in the thrust generating device, as viewed from above. FIG. 16A shows the vicinity of the exhaust hole at the rear of the box-shaped nacelle. ) Is a “deflecting plate having a rotational axis perpendicular or oblique to the longitudinal direction line of the aircraft and for changing the direction of the aircraft in the left-right direction”. It is provided inside the casing located behind the rotor blade.
FIG. 16B is a simplified cross-sectional view of FIG. 16A viewed from the side, and the exhaust is deflected in the left-right direction by the rotating shaft of FIG.
FIG. 17 shows an example of a simplified diagram of a “turbine for gas turbine for connection or integral configuration with a rotating body” according to claim 8 of the present invention, which is connected to a shaft (72b) connected to the turbine (72a). A rotor blade having a plurality of blades (72d) fixed radially on the outer periphery of a rotor (72c) that fixes a plurality of blades is an example in which a generator magnet (72e) is installed.
17 (A) is provided in a portion corresponding to (2) in FIG. 1, and (73) is for the rotor according to claim 1 of the present invention, which rotates reversely with the rotor (72a) for a low-pressure compressor. The outer ring (74) is the outer ring for a rotor according to claim 1 which rotates in the reverse direction with the rotor (75) for a high-pressure compressor, and the rotational directions of (72c) and (75) are the same. Even in the reverse direction, the direction of rotation is arbitrary by the manufacturer.
(76) is a bearing (76) of (72a-e) and a stationary blade (77) that supports the bearing, and the type thereof is not limited, such as equipment of a fuel injection device for a reburner (afterburner).
FIG. 17B shows a mechanism for generating electric power by rotating the rotor, and FIG. 17C shows a mechanism for generating electric power by rotating the shaft.
Regarding the reburner, page 117 of Non-Patent Document 36, pages 139 and 165 and 342 of Non-Patent Document 39, page 53 of Non-Patent Document 38, page 112 of Non-Patent Document 40, See page 126, etc.
Embodiments of the present invention are as follows.
1. As long as the conditions of the claims of the present invention are satisfied, the shape, material, and type of structure are not limited.
2. Types of the control device for operating the device of the claims of the present invention are not limited as long as they satisfy the claims of the present invention, such as hydraulic pressure, air pressure, motor, screw and gear.
3. In the axial flow compressor of the present invention, a low-pressure compressor and a high-pressure compressor are mainly used for explanation, but the structure of the present invention can also be used in an intermediate-pressure compressor, and the compressor may be of an axial flow type. The type is not limited.
4). The types of combinations of the claims of the present invention with other effects and functions of devices and things are not limited.

L: component of force perpendicular to the flow, Le: leading edge of the blade, Te: trailing edge of the blade, ch: chord, chL: chord length, V: flow direction of fluid, α: angle of attack, bup : Upper surface of blade, bun: lower surface of blade, b: blade, bL: boundary layer, ef: mainstream, se: separation region, fw: front blade, rw: rear blade
X: line parallel to the rotation axis, Y: vertical line of the jet engine in a direction perpendicular to the line parallel to the rotation axis,
w: blade, W1: blade located in the front row, W2: blade located in the back row, LX: axial reference line, LY: radial line of the axial compressor, Sa: stagger angle, sw: stationary blade, R :rotor,
1: Rotating body of axial compressor, 2: casing, 3: space for bypass, 3 ′: space constituted by nozzles for high temperature core flow, 4: combustor, 1f: nose cone, 1r: tail cone 1Lr: low-pressure compressor, 2L: outer casing, 2H: high-pressure casing, 1Hr: high-pressure compressor, 1Ht: high-pressure turbine, 1Lr: low-pressure compressor, 1Lt: low-pressure turbine, af: reburning device, af1: Fuel injection strut, af2: flame holder,
w: blade / blade, sw: stationary blade, R rotor,
5: Rotating shaft or bearing, 6: Blade of rotor blade, 7: Outer ring for power, 8: Magnet, 9/10: Outer ring for power or outer rotor for power, 9 ', 10': Teeth for gears, 11.13: Gear, 12.14: Rotating shaft, 14 '': Transmission, 15: Tapered rotor blade fixing part / rotor, 16: Blade, 17F / 18F / 17F '/ 18F': Forward , 17R, 18R, 17R ′, 18R ′: Rear bearing, 19: Bearing, 20: Conducting coil, 21: Magnet rotor, 22: Rotating shaft, 23: For supporting the rotor on the outer periphery of the electric rotor blade Casing, 23F: front ring-shaped fixing part, 23R: rear ring-shaped fixing part, 24: structural part capable of rolling the bearing, 25: stationary blade, 26: cylindrical rotating rotor, 27: blade , 28: Electric Coil, 29: magnet rotor, 30: legs for support,
IR / OR: Compressor blade, SW: Stator blade, Ca: Casing,
39: Rotating shaft, 40: Moving blade, 41: Coil for rotation, 42: Stationary blade, 43: Connecting portion, 44: Ring-shaped rotating shaft, 45: Casing of box-shaped thrust generating device, 46: Moving blade , 47, 47 ', 47 ", 47'", 47 "": Thrust generating device lid, 48: Vertically penetrating hole, 48 ': Air venting hole, 49: Thrust generating A rotating shaft that connects the lid of the device for equipment and the box of the device for thrust generation,
50: Near the elevator at the rear of the horizontal tail, 50 ': Horizontal stabilizer, 50 ": Rear structure of the aircraft, 51: Device for generating thrust, 52: Robot arm, 53/54: Actuator,
55, 56: Actuator, 57: Door plate, 58: Rotating shaft, 59: Rod, 60: Cylinder, 60 ': Rotating shaft, 61: Rod support, 61': Rotating shaft, 62: Thrust generation of the present invention Device 62 ': Ring for rotation, 63: Through-hole, 64: Near the horizontal tail, 65: Lid covering the opening, 66: Connection part with arm, 67: Wheel, 68: Guide rail, 69: Box shape Nacelle, 70: deflection plate, 71: rotating shaft

Claims (8)

It is composed of a moving blade with a row of multiple twisted and angled blades,
A rotating body that rotates in one of a rotating body that rotates right and a rotating body that rotates counterclockwise is a rotating body for forward rotation, and the other rotating body is a rotating body for reverse rotation.
The rotation centers of the forward rotation rotor and the reverse rotation rotor described above are concentric or nearly concentric in the front-rear direction of the rotating shaft of the rotor blade, and are alternately combined in multiple stages to overlap each rotation direction. A rotor for an axial compressor that flows gas from the front to the rear by rotating it,
And, for exhausting gas in the direction from the front to the rear of the rotary shaft of the rotor for the axial flow compressor, the cylindrical shape surrounding the outer periphery of the rotor for the axial flow compressor and penetrating in the front-rear direction of the rotary shaft A casing having a hole structure and for rotating and supporting the rotor for an axial compressor described above,
In the axial flow compressor having the following structure:
A plurality of blades arranged in a row on the inner circumference of the outer ring for power or the outer rotor for power are arranged and fixed radially in the inner direction of the outer ring for power or outer rotor for power to constitute a moving blade, A rotating body constituting a rotor power member on the outer peripheral side of a row of blades of a moving blade, wherein a structure part for a bearing for rotating and supporting the moving blade is formed on the outer peripheral side or inner peripheral side of the moving blade ,
as well as,
A plurality of blades arranged in a row on the outer circumference of the power disk or power inner rotor are arranged and fixed radially outwardly of the power disk or power inner rotor to form a moving blade. A rotating body constituting a rotor power member on the inner peripheral side of a row of blades of a moving blade, wherein a structure for a bearing for rotating and supporting the moving blade is formed on the inner peripheral side or outer peripheral side of the blade;
An axial flow type thrust generating device characterized by comprising: In each row of rotor blades composed of a plurality of blades constituting the rotor blades of the rotor for an axial flow compressor according to claim 1,
Axial flow compression comprising a shroud or a connection ring for reinforcing reinforcement between adjacent blades in a row of blades on a rotating circle located at the same or substantially the same distance from the rotation center of the rotor blades of the rotating body. Rotor for machine,
An axial flow type thrust generating device characterized by comprising: The casing according to claim 1,
In the rotating body having the rotor outer ring or the rotor outer rotor described above, the structure of the rotating body is arranged on the outer peripheral side of the row of blades of the moving blade with a structure for bearings for rotating and supporting the moving blade. A structural part for the inside of the casing, comprising a structural part for bearings for rotation and support,
An axial flow type thrust generating device characterized by comprising: The casing according to claim 1,
In a rotating body having an outer ring for rotor or an outer rotor for rotor, a structure part for a bearing for rotating and supporting a rotor blade on the inner peripheral side of a row of blades of a rotor blade, or a rotor disk Alternatively, in a rotating body having an inner rotor for a rotor, a bearing structure for rotating and supporting the rotor blades on the inner peripheral side of the row of blades of the rotor blades, and a bearing for rotating and supporting the rotor body The structure part for
A casing structural portion in which a plurality of stationary blades or struts are radially arranged and fixed on the circumference in the casing side direction from the bearing structural portion that is not on the rotating body side,
An axial flow type thrust generating device characterized by comprising: In the structure of the rotor for an axial compressor and the casing according to any one of claims 1 to 4,
A rotor in the rotor for an axial compressor described above, comprising a rotor-forming magnet or magnetic body for power generation,
as well as,
A casing structure portion in the vicinity of the above-described rotor, which includes a stator conductor corresponding to the above-described rotor,
An axial flow type thrust generating device characterized by comprising: In the structure of the rotor for an axial compressor and the casing according to any one of claims 1 to 4,
A rotor for a rotor in which the outer ring for power of the rotor for an axial compressor or the gear teeth for power transmission is formed on the circumference of the outer rotor for power,
as well as,
A casing structure near the power outer ring or power outer rotor, which constitutes a gear device for transmitting power to the rotor for the rotor,
An axial flow type thrust generating device characterized by comprising: In the structural part of the rotor for an axial compressor and the casing according to any one of claims 1 to 6,
A rotating body in which a magnet or a magnetic body is configured as a constituent part of the rotating body,
as well as,
A casing structure near the above-mentioned rotating body, in which a conductor is configured for power or power generation corresponding to a magnet similar to the magnet of the above-mentioned rotating body or a brake by electric resistance,
An axial flow type thrust generating device characterized by comprising: In the rotor for an axial compressor according to claim 1,
Connection with the rotor constituting the rotor power member on the inner peripheral side of the rotor blade row or connection with the rotor constituting the rotor power member on the outer peripheral side of the rotor blade row A turbine for a gas turbine,
An axial flow type thrust generating device characterized by comprising:

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