KR100800117B1 - Gyro axial flow turbine Compressor - Google Patents

Abstract

According to the present invention, an insertion hole is formed at both ends, and a casing having a space portion therein; A rotating shaft inserted into the casing through the insertion hole and rotating; A plurality of rotary rotors disposed along the rotational shaft in a longitudinal direction and fixedly coupled to the rotary shaft to rotate together with the rotary shaft, and a plurality of blades disposed along the circumference thereof; And a plurality of free-fixed rotors disposed alternately with the rotary rotor along the longitudinal direction on the axis of rotation, rotatably coupled to the axis of rotation so as not to be affected by the rotation of the axis of rotation, and with a plurality of blades disposed around the axis of rotation. An integrated axial turbine compressor is provided. According to the disclosed integrated axial turbine compressor, the free-fixing rotor corresponding to the conventional stator blade is integrally provided on the rotating shaft, thereby preventing fatigue destruction due to the rotating stall of the rotating rotor even during operation in a low speed or ultra high speed region, and at the same time operating at a constant speed. We can expect efficiency equal to city.

Axial flow turbine, compressor, rotor, bearing

Description

Integrated axial flow turbine compressor

1 is a schematic diagram of a gas turbine engine,

2 is a schematic diagram of a conventional axial turbine compressor,

3 is a cross-sectional perspective view of an integrated axial turbine compressor according to an embodiment of the present invention;

4 is a cross-sectional view of the integrated axial turbine compressor shown in FIG. 3,

5 is a schematic view showing the configuration of the stage of the conventional axial turbine compressor shown in FIG.

6 is a view showing an incidence angle increasing mechanism in a low speed rotation region of the conventional axial turbine compressor shown in FIG.

FIG. 7 is a view illustrating a rotating stall generating mechanism of the conventional axial turbine compressor illustrated in FIG. 2;

8 is a view showing the direction of movement of the rotary rotor and the free-fixed rotor shown in Figure 3,

9 is a cross-sectional view of an integrated axial turbine compressor according to another embodiment of the present invention.

<Explanation of symbols for the main parts of the drawings>

100,200 ... integral axial turbine compressor 110 ... casing

111 ... Inlet 112,113 ... Boss section

114 ... Guide blade 120,220 ... spindle

130 ... rotary rotor 131,141 ... blade

140 ... Fixed rotor 142 ... Bearings

150 ... axial bearing

The present invention relates to an axial flow turbine compressor, and more particularly to an integrated axial turbine compressor for use in a gas turbine engine.

1 is a schematic diagram of a gas turbine engine.

In general, a gas turbine engine is used to provide propulsion force for aircraft, ships, automobiles, and the like, or is used for industrial purposes such as power generation. As shown in FIG. 1, the compressor 10, the combustion chamber 20, and the turbine 30 are shown in FIG. ). The gas turbine engine 40 uses the compressor 10 to compress air while flowing in the axial direction, introduces compressed air thus compressed into the combustion chamber 20, and then, in the combustion chamber 20, the combustion chamber 20. The gas is mixed with the fuel sprayed therein to be ignited to generate a high temperature gas, and power is obtained by driving the turbine 30 using the generated high temperature gas. Meanwhile, a part of the compressed air compressed by the compressor 10 is collected from the compressor 10 and used to cool the apparatus located at the rear end such as the combustion chamber 20 and the turbine 30.

As described above, the compressor 10 provided in the gas turbine engine 40 compresses the air while flowing in the axial direction, thereby converting the mechanical energy supplied from the turbine 30 into the pressure energy of the air, It is to increase the potential (potential), it is heated in the combustion chamber 20 of a limited volume and then to increase the air to be expanded while passing through the turbine 30 to the maximum pressure.

The compressor 10 may be classified into a centrifugal compressor and an axial compressor. Among these, the axial compressor may handle a large amount of air and may be manufactured in multiple stages to increase the pressure ratio. It is possible to use, and high pressure ratio and efficiency of inlet and outlet are used in high performance engine.

2 is a schematic diagram of such a conventional axial turbine compressor.

Referring to the drawings, the conventional axial turbine compressor 10, a stator (11) forming the appearance of the compressor (10), a rotor shaft (Rotor shaft) 12 for rotating the inside of the stator (11), the rotary shaft And a stator blade (15) mounted on the stator (11) and a rotor (13) on which the rotor blades (14) are mounted, rotated and rotated along the outer circumferential surface thereof. The rotor blade 14 and the stator blade 15 are alternately arranged along the longitudinal direction of the rotation shaft 12.

The conventional axial turbine compressor 10 generally has a compression ratio of about 1.1 to 1.3: 1 in one stage, so that the axial turbine compressor 10 should be designed in 12 to 20 stages (stage = rotor blade + stator blade) in order to be used in an aircraft or industry. In this case, the rotor blades 13 and the stator blades 14 need to be alternately assembled in the manufacturing and assembling process. In particular, since the attachment process of the stator blades 14 is very difficult, it is difficult to maintain precision. Moreover, since the smaller the axial turbine compressor, the greater the difficulty, the conventional axial turbine compressor 10, despite the high efficiency, the small and medium size has a disadvantage of low economic efficiency.

In addition, in the conventional axial turbine compressor 10, the inflow incident angle of the rotor blade 14 increases in low speed operation, so that a rotating stall occurs in the rotor blade 14, so that low-speed fatigue failure may occur. In the operation of the ultra-high speed region, the inflow incident angle of the rotor blade 14 is excessively reduced, and the phenomenon that the efficiency is lower than that at the constant speed operation may occur.

In order to compensate for these disadvantages, there is a method of changing the angle of the stator blade 15 according to the speed of the compressor 10, but the actual application is difficult due to the difficulty in increasing the manufacturing cost and maintenance.

The present invention was created in order to solve the above-mentioned problems, so that the manufacturing cost is low, and can be easily manufactured even in the small and medium size, so that high efficiency can be achieved without the fear of fatigue failure even in the operation of the low speed or the ultra high speed region. It is an object of the present invention to provide an integrated axial turbine compressor having improved structure.

Other objects and advantages of the invention will be described below and will be appreciated by the embodiments of the invention. In addition, the objects and advantages of the invention may be realized by the means and combinations indicated in the claims.

An integrated axial turbine compressor of the present invention for achieving the above object, the insertion hole is formed at both ends, and the casing having a space therein; A rotating shaft inserted into the casing and rotating through the insertion hole; A rotating rotor disposed in the longitudinal direction on the rotating shaft, fixedly coupled to the rotating shaft to rotate together with the rotating shaft, and having a plurality of blades disposed along a circumference thereof; And a plurality of free-fixing parts disposed alternately with the rotary rotor along a longitudinal direction on the rotary shaft, rotatably coupled with respect to the rotary shaft so as not to be affected by the rotation of the rotary shaft, and having a plurality of blades disposed around the rotary shaft. It includes a rotor.

Here, the blades disposed in the rotary rotor and the blades disposed in the free-fixed rotor preferably have opposite inclinations.

In addition, the free-fixed rotor is preferably coupled to the rotating shaft via an air bearing.

In addition, the free-fixed rotor is preferably cooled and lubricated by the atomized lubricating oil inside the rotating shaft using the air compressed through the final stage free-fixed rotor.

Here, the rotary shaft inside, the flow path hole extending from the open end of the rotary shaft to the inside of the rotary shaft in the longitudinal direction, and provides a passage for the lubricant oil sprayed from the outside into the rotary shaft; An air inlet hole extending radially from the passage hole to the surface of the rotating shaft and providing a passage through which the compressed air, which is compressed through the rotating rotor and the free-fixing rotor, flows into the passage hole; And a plurality of injection holes disposed at the contact portion of the rotating shaft and the free-fixing rotor, and extending radially from the flow path hole to the surface of the main shaft to provide a passage through which lubricant oil mixed with compressed air is injected. .

Hereinafter, exemplary embodiments of the present invention will be described in detail with reference to the accompanying drawings. Prior to this, terms or words used in the present specification and claims should not be construed as being limited to the common or dictionary meanings, and the inventors should properly explain the concept of terms in order to best explain their own invention. Based on the principle that can be defined, it should be interpreted as meaning and concept corresponding to the technical idea of the present invention.

Therefore, the embodiments described in the specification and the drawings shown in the drawings are only the most preferred embodiment of the present invention and do not represent all of the technical idea of the present invention, various modifications that can be replaced at the time of the present application It should be understood that there may be equivalents and variations.

3 is a cross-sectional perspective view of an integrated axial turbine compressor according to an embodiment of the present invention, and FIG. 4 is a sectional view of the integrated axial turbine compressor shown in FIG.

3 and 4, the configuration of the integrated axial turbine compressor according to one embodiment of the present invention will be briefly described.

3 and 4, the integrated axial turbine compressor 100 according to an embodiment of the present invention, the casing 110, the rotary shaft 120, the rotary rotor 130 and the free-fixed rotor 140.

First, the casing 110, which forms the appearance of the integrated axial turbine compressor 100 according to an embodiment of the present invention, which is a space in which the rotating shaft 120 and the rotation and free-fixed rotors 130 and 140 are disposed. A space portion (not shown) is formed, and at one end, a passage through which air is introduced into the casing 110 from the outside is formed, and at the other end, the compressed air is introduced into the casing 110 and discharged to the outside of the casing 110. A passage is formed.

In more detail, the bosses 112 and 113 forming the insertion holes 111 are positioned at both ends of the casing 110, respectively, and the bosses 112 and 113 are open around the casing 110. Guide blades 114 for guiding the inflow path of air introduced into the casing 110 are disposed around the boss part 112 positioned at one end. Here, the guide blade 114 guides the inflow path of the air and at the same time serves to support the boss portion 112 to the casing 110. On the other hand, each of the bosses 112 and 113, the shaft bearing 150 is mounted, respectively, the inside of the shaft bearing 150 is in communication with the insertion hole 111.

Next, the rotating shaft 120 is inserted into the casing 110 through the insertion holes 111 formed at both ends of the casing 110, and penetrates through the inside of the casing 110 through the insertion holes 111, and a boss. It is supported by the axial bearing 150 mounted inside each of the parts 112 and 114, and rotates in the axial direction.

In addition, the rotary rotor 130 is fixedly coupled to the rotary shaft 110 and rotates together with the rotary shaft 110, a plurality is disposed along the longitudinal direction of the rotary shaft 110, such a rotary rotor 130 A plurality of blades 131 are mounted along the circumference thereof.

Finally, the free-fixed rotor 140, which is rotatably coupled with respect to the rotary shaft 110 so as not to be affected by the rotation of the rotary shaft 110, the rotary rotor 130 along the longitudinal direction of the rotary shaft 110 Multiples are placed one by one, alternately with. The free-fixed rotor 140, like the rotary rotor 130, a plurality of blades 141 are mounted along the circumference, each of the blades 141 mounted to the free-fixed rotor 140, It has a slope opposite to the blade 131 mounted to the rotary rotor 130. The free-fixed rotor 140 is preferably coupled to the rotating shaft 110 via a bearing 142 in order to be rotatably coupled with respect to the rotating shaft 110. That is, by coupling the bearing 142 inside the free-fixed rotor 140 and inserting the rotary shaft 110 into the bearing 142, the free-fixed rotor 140 is adapted to the rotation of the rotary shaft 110. It is to be rotatably coupled to the rotating shaft 110 so as not to be affected.

Hereinafter, the operation relationship of the integrated axial turbine compressor 100 according to the embodiment of the present invention having such a configuration will be briefly described.

In the integrated axial turbine compressor 100 according to an embodiment of the present invention, the rotary shaft 120 is rotated in a predetermined direction by receiving a motive force such as an engine or an electric motor, according to the rotary rotor 130 coupled to the rotary shaft 120 ) Also rotates in the same direction as the rotation shaft 120 rotates. Accordingly, the air sucked through the flow path formed between the guide blades 114 continues to be sucked by the forced feed force of the rotary rotor 130, the rotary rotor 130 and the free-fixed rotor 140 of each stage While passing through the flow path formed between the blades (131, 141), it is decelerated and pressed.

In this case, the free-fixed rotor 140 is rotatably coupled with respect to the rotation shaft 110 so as not to be affected by the rotation of the rotation shaft 110, and each blade 141 mounted thereto is mounted on the rotation rotor 130. Since it has a slope opposite to that of the mounted blade 131, in the state that does not rotate together with the rotary rotor 130, the rotary rotor 130 by the axial energy of the air flow generated by the rotary rotor 130 Will rotate in the opposite direction of rotation. The opposite rotational speed of the free-fixed rotor 140 depends on the rotational speed of the rotary rotor 130 that rotates in accordance with the rotation of the rotary shaft 120. That is, when the rotary rotor 130 rotates at a higher speed, the free-fixed rotor 140 also rotates faster in the opposite direction of rotation of the rotary rotor 130 by the axial energy of the air stream. .

The integrated axial turbine compressor 100 according to the embodiment of the present invention having such a configuration, as described above, is provided with a free-fixed rotor 140 corresponding to the conventional stator blades integrally on the rotating shaft, thereby, the conventional axial turbine There is no need for the difficult stator blade attachment process required in the manufacture and assembly of the compressor, which makes it easy to manufacture, greatly reduces the manufacturing cost, and makes it easy to manufacture in a small size, and also has a simple structure and easy maintenance and repair. .

5 is a schematic view showing the configuration of the stage of the conventional axial turbine compressor shown in Figure 2, Figure 6 is a view showing the angle of incidence increasing mechanism in the low-speed rotation region of the conventional axial turbine compressor shown in Figure 2, Figure 7 Figure 2 is a view showing a rotating stall generating mechanism of the conventional axial turbine compressor shown in Figure 2, Figure 8 is a view showing the direction of movement of the rotary rotor and the free-fixed rotor shown in FIG.

Here, the same reference numerals as in the above-described drawings indicate the same members having the same function.

5 to 8, the operation mechanism of the integrated axial turbine compressor according to the preferred embodiment of the present invention will be described in detail in comparison with the conventional axial turbine compressor.

First, if only one stage is taken and analyzed from a cross section cut into a cylindrical surface around a rotating shaft of a conventional axial turbine compressor, it may be displayed as shown in FIG. 5.

here,

The symbol C stands for absolute speed, W for relative speed, U for the circumferential speed of the rotor blades,

Subscript 1 denotes a rotor blade inlet, 2 rotor blade outlet (stator blade inlet), 3 stator blade outlet (next stage rotor blade inlet), a denotes an axial component, and u denotes a circumferential component.

In this analysis, since the pressure ratio of the first stage is as small as 1.1 to 1.3, it is assumed that the air is incompressible, and the velocity component due to the centrifugal force in the cross section from the rotor blade inlet to the stator blade outlet is ignored.

Referring to the drawings, the shape of the rotor blade 14 formed on the outer circumferential surface of the rotor 13 provided in a conventional conventional axial compressor is intentionally configured to have a larger inlet angle (B ₁ ) than the outlet angle (B ₂ ). In addition, the flow path between the adjacent rotor blades 14 is configured such that the outlet area is gradually enlarged compared to the inlet area. On the other hand, the stator blade 15 fixed to the stator 11 is appropriately formed in the reverse direction with respect to the rotor blade 14 so that the flow direction of air is switched. Thus when synthesis of the circumferential velocity U at the time of entering the flow path entrance between the air flow absolute velocity C ₁ in an amount of rotor blade 14 forms the a ₁ angle, the absolute velocity C ₁ and the rotor blade 14, and along Relative velocity for vector W ₁ And the inlet angle B ₁ , since the outlet area of the rotor blade 14 is larger than the inlet area, the relative speed W ₁ is decelerated to W ₂ , thereby increasing the pressure inside the rotor. At the exit of the rotor blades 14, the relative speed W ₂ and the circumferential speed U are combined to become the outlet absolute speed C ₂ and increased relative to the original C ₁ , whereby the air passing through the rotor blades 14 increases in pressure and speed. Increases. The air passing through the rotor blades 14 passes through the flow path formed in the stator. At this time, since the inlet angle a ₂ of the stator blade 15 is larger than the outlet angle a ₃ , the air flow rate is C ₂ to C. _As it decelerates to ₃ , part of the dynamic pressure is converted to static pressure. As described above, the conventional axial turbine compressor forms such a rotor blade 14 and a stator blade 15 in a plurality of stages to obtain high pressure in the process of changing the air flow direction and increasing or decreasing the absolute speed and the relative speed while passing through each stage. It has a mechanical configuration.

In conclusion, the rotor disposed with the stator of the conventional method, in some cases to obtain a pressure increase effect due to the deceleration of the relative speed according to the shape of the rotor blade 14, the critical role is the rotational speed of the rotor blade 14 According to this, the suction flow is secured to the maximum, and forcedly transferred to obtain a pressure increase effect. On the other hand, the fixed-chain stator decelerates the flow rate of air and obtains a pressure increase effect. By changing the flow of air, the stator does not easily flow back to the rotor of the next stage. It is complementary to the rotor by acting to obtain a pressure increase effect.

However, in the above-described conventional axial turbine compressor, as indicated above, in low speed operation, rotating stall may occur and low-speed fatigue failure may occur. Looking at the cause of the rotating stall by the low speed rotation in the conventional axial turbine compressor,

입사각이 증가하고 블레이드의 뒷면에 층류 박리가 발생하여 실속에 이르게 된다.In the conventional axial turbine compressor, since the pressure ratio from the turbine inlet to the outlet reaches 15 to 30, the density change is very large. Therefore, the flow path area in the turbine is largely throttled from the inlet to the outlet in response to the increase in density. However, in the low-speed rotation region, although the pressure increase is small and a sufficient density increase is not obtained, the flow path cross section is throttled, so that the flow resistance becomes large and the flow is closed. As a result, at the stage near the inlet of the turbine, the axial flow rate is reduced to the blades.

The angle of incidence increases and laminar delamination occurs on the back of the blade leading to stall.

As shown in FIG. 6, when the incident angle increase process at low speed rotation using the speed triangle is compared with the speed triangle of the design point at the normal rotation, the mass flow rate at the design point is increased due to the increase in density. It is proportional to approximately 1.4 wins. In addition, since the mass flow rate is directly proportional to the axial flow rate, the axial flow rate is also proportional to 1.4 power of the rotation speed. At this time, since the circumferential speed is directly proportional to the number of revolutions, the speed change process of the airflow is shown in the form of a speed triangle indicated by a dotted line during the low-speed rotation, and the angle of incidence of the airflow to the blade is increased by Δθ than the design value.

According to this mechanism, as described above, when the axial compressor having a high pressure ratio is operated in a low-speed rotation region, since the pressure ratio is small, the narrow flow path at the rear end becomes a resistance and the air volume is limited, and in the front blade, the design state The angle of incidence becomes larger, causing stall. When some of the blades stall, as shown schematically in FIG. 7, the separation zone of the blade b narrows the flow path between the blades, so that the direction of air flow flowing into the blades before and after the blades changes, thereby changing the blades. In (c), incident angle becomes small and peeling is suppressed. On the contrary, in the blade (a) which has not stalled yet, the incident angle becomes large, and a new stall occurs. In this way, the stall area propagates at a substantially constant speed in the direction of the arrow. The propagation direction of this stall area is the opposite direction to the rotation direction, and the propagation speed of the stall to the subsequent blade is 30 to 80% of the rotation speed. Therefore, in the stationary coordinate system, the stalled rotor blade appears to rotate at a speed of 70 to 20% of the rotational speed of the blade in the rotational direction. This phenomenon is called turning stall. In addition, when the propagation speed of the stall is the same as the rotation speed, the stalled rotor blade is observed in a stationary state. When such a stall stall occurs, vibration stress of unexpected strength acts and is directly related to fatigue failure of the rotor blade.

On the other hand, when the inlet flow rate is increased by increasing the rotational speed of the rotor to obtain a high pressure vaguely, the deceleration of the flow rate acting as a pressure increase factor in the upper stator acts as a back pressure, which impedes the intake flow rate. The pressure of the expected value cannot be obtained compared to the rotation speed.

For this reason, in the conventional axial turbine compressor 10 as shown in FIG. 4, the operating value and design value are already determined according to the shape of the rotor blade 14 and the stator blade 15 and the degree of the bevel angle. There is an inefficient problem in the rotation speed range below and above.

Referring to Figure 8, looking at the operating mechanism of the integrated axial turbine compressor according to a preferred embodiment of the present invention, which complements the problems of the conventional axial turbine compressor,

An integrated axial turbine compressor according to an embodiment of the present invention, in place of the stator blade of the conventional axial turbine compressor, has a free-fixed rotor equipped with a plurality of blades 141 having an inclination opposite to that of the rotor of the rotating rotor. have. Such a free-fixed rotor has a feature of being free regardless of the rotation of the rotating shaft because it is coupled to the rotating shaft using a bearing. With this feature, the axial energy of the air flow generated through the blade 131 of the rotary rotor can rotate the free-fixed rotor in the direction opposite to the rotation direction of the rotary rotor.

The reverse rotational force of the free-fixed rotor causes an effect of reducing the incidence angle of inflow into the next rotary rotor during operation in the low-speed rotation region, thereby preventing the turning stall caused by laminar flow separation. In addition, the reverse rotational force of the free-fixed rotor during the operation of the ultra-high speed region restrains the occurrence of back pressure by forcibly transferring the air introduced from the preceding rotary rotor to the next rotary rotor.

Therefore, according to the integrated axial turbine compressor according to an embodiment of the present invention having the above characteristics, even when operating in the low speed or ultra high speed region, while preventing fatigue failure due to the rotating stall of the rotary rotor and at the same time constant speed operation You can expect efficiency.

9 is a cross-sectional view of an integrated axial turbine compressor according to another embodiment of the present invention.

Here, the same reference numerals as in the above-described drawings indicate the same members having the same function.

Referring to the drawings, the integrated axial turbine compressor 200 according to another embodiment of the present invention, as lubricating means for the free-fixed rotor 140 coupled to the rotating shaft 220 by a bearing 142, The flow path hole 221, the air inlet hole 222, and the plurality of injection holes 223 are formed in the rotary shaft 220.

More specifically, the flow path hole 221 is a passage through which the lubricant oil sprayed from the outside flows into the rotary shaft 220, and the rotary shaft 220 extends along the length direction from one end of the opened rotary 220 shaft. Extends inside).

In addition, the air inlet hole 222 is a passage through which a portion of the compressed air compressed through the rotary rotor 130 and the free-fixed rotor 140 of the final stage flows into the flow path hole 221. However, it is preferably formed in the vicinity of the free-fixed rotor 140, and radially extends from the flow path hole 221 to the surface of the rotating shaft 220, it is in communication with the flow path hole 221.

The injection hole 223 is a passage through which the lubricating oil mixed with the compressed air is injected into the contact portion of the rotary shaft 220 and the free-fixed rotor 140, and the rotary shaft 220 and the free-fixed rotor 140. It is preferably formed in the contact portion of the rotary shaft 220 and the contact portion of the bearing 142, radially extending from the flow path hole 221 to the surface of the rotating shaft 220, and the flow path hole 221 and It is in communication.

Hereinafter, the lubrication system of the integrated axial turbine compressor 200 according to another embodiment of the present invention will be briefly described.

Lubricant is injected into the flow path hole 221 through an open end of the rotating shaft 220 for lubrication of the free-fixed rotor 140 coupled to the rotating shaft 220 by the bearing 142. For the supply of such lubricating oil, a rotary joint (not shown) may be used. In this way, the lubricating oil injected into the passage hole 221 is mixed with the compressed air introduced through the air inlet hole 222. The compressed air is compressed through the rotary rotor 130 and the free-fixed rotor 140 of the final stage, and flows through the air inlet hole 222 formed in the vicinity of the final free-fixed rotor 140. Flows into the ball 221. The compressed air introduced in this way is mixed with the lubricating oil in the passage hole 221 to atomize the lubricating oil.

The lubricating oil atomized through the above process is injected from the flow path hole 221 to the surface of the rotating shaft 220, more specifically, the contact portion between the rotating shaft 220 and the bearing 142 through the injection hole 223. Not only does lubrication between the 220 and the bearing 142, but also performs the role of cooling at the same time. In other words, in the integrated axial turbine compressor 200 according to another embodiment of the present invention as described above, after atomizing the lubricating oil using high pressure compressed air, the lubricating oil of the atomized state is rotated and the bearing ( By having a lubrication system sprayed on the contact portion of the 142, there is an advantage that the cooling and lubrication of the rotating shaft 220 and the bearing 142 can be performed simultaneously.

As mentioned above, although this invention was demonstrated by the limited embodiment and drawing, this invention is not limited by this, The person of ordinary skill in the art to which this invention belongs, Of course, various modifications and variations are possible within the scope of equivalents of the claims to be described.

According to the integrated axial turbine compressor of the present invention, the free-fixing rotor corresponding to the conventional stator blade is integrally provided on the rotating shaft, thereby preventing fatigue failure due to the rotating stall of the rotating rotor even during operation in a low speed or ultra high speed region. Efficiency equivalent to that in constant speed operation can be expected.

In addition, there is no need for the difficult stator blade attachment process required in the manufacturing and assembling of the conventional axial turbine compressor, and it is easy to manufacture, greatly reduces the manufacturing cost, and is easy to manufacture in small size, and the structure is simple to maintain and repair. There is an easy advantage.

In addition, after atomizing the lubricating oil by using a high-pressure compressed air, by having a lubricating system for spraying the lubricating oil in the atomized state to the contact portion of the rotating shaft and the bearing, there is an advantage that cooling and lubrication can be performed simultaneously.

Claims (5)

An insertion hole is formed at both ends and a casing having a space portion therein; A rotating shaft inserted into the casing and rotating through the insertion hole; A rotating rotor disposed in the longitudinal direction on the rotating shaft, fixedly coupled to the rotating shaft to rotate together with the rotating shaft, and having a plurality of blades disposed along a circumference thereof; And A plurality of free-fixed rotors disposed alternately with the rotary rotor along a longitudinal direction on the rotary shaft, rotatably coupled with respect to the rotary shaft so as not to be affected by the rotation of the rotary shaft, and having a plurality of blades disposed around the rotary shaft; Integrated axial turbine compressor comprising a. The method of claim 1, Integral axial turbine compressor, characterized in that the blades disposed in the rotary rotor and the blades disposed in the free-fixed rotor have opposite inclinations. The method of claim 1, And said free-standing rotor is coupled to said rotating shaft via an air bearing. The method according to claim 1 or 3, And said free-fixed rotor is cooled and lubricated by liquefied lubricating oil inside the rotating shaft using compressed air passing through the final stage free-fixed rotor. According to claim 4, Inside the rotating shaft, A flow path hole extending from the open end of the rotating shaft in the longitudinal direction to the inside of the rotating shaft and providing a passage through which the lubricating oil sprayed from the outside flows into the rotating shaft; An air inlet hole radially extending from the passage hole to the surface of the rotating shaft and providing a passage through which the compressed air, which passes through the rotating rotor and the free-fixing rotor, flows into the passage hole; And A plurality of injection holes disposed at a contact portion of the rotation shaft and the free-fixing rotor, and extending radially from the flow path hole to the surface of the rotation shaft to provide a passage through which compressed air is atomized and mixed with compressed air; Integrated axial turbine compressor.

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