WO2023241021A1

WO2023241021A1 - Gas jet stream splitting-type rotor supercharged gas turbine

Info

Publication number: WO2023241021A1
Application number: PCT/CN2023/000072
Authority: WO
Inventors: 韩培洲
Original assignee: 韩培洲
Priority date: 2022-06-14
Filing date: 2023-06-12
Publication date: 2023-12-21
Also published as: CN117266987A

Abstract

A gas jet split stream-type rotor supercharged gas turbine, which comprises a gas compressor (21) and a turbine (23) connected by means of a mechanical shaft; a rotor (25) having multiple rows of combustion chambers (26) is arranged between the gas compressor and the turbine, the rotor being arranged in a rotor casing (29); in gas outlets provided on the rotor casing, work-producing gas of the highest temperature and pressure generated in the combustion chambers (26) that is in a portion of gas outlets and passes through corresponding gas conveying pipes first generates some thrust by means of a gas jet or driving additionally-provided outer ring blades (36); the remaining work-producing gas in the combustion chamber passes through another portion of gas outlets and corresponding gas conveying pipes and drives the turbine (23). Work-producing gas generated in the combustion chamber undergoes gas jet stream splitting, which improves the work efficiency of the rotor supercharged gas turbine, and there is also no need to use highly temperature-resistant materials to manufacture turbine blades because the remaining work-producing gas in the combustion chambers has a lower temperature and pressure, thereby also reducing the manufacturing costs of the gas turbine.

Description

Jet split rotor supercharged gas turbine

Technical Field The present invention relates to a rotor supercharged gas turbine, in particular to a jet split rotor supercharged gas turbine.

Background Technology In the rotor supercharged gas turbine with application number 202011068701.0, although the structure of the multi-row combustion chamber rotor is optimized, fuel and air can form a homogeneous fuel atomization mixture for combustion. The discharged high-temperature and high-pressure power gas will all be sprayed into the turbine to do power. Although the shaft power generated by the gas turbine is very large, in the rotor supercharged gas turbine used for aircraft, the power gas energy generated by the rotor combustion chamber is partially reduced. Direct post-jet and jet splitting may achieve better propulsion effects.

SUMMARY OF THE INVENTION The purpose of the present invention is to provide a jet-splitting rotor supercharged gas turbine, which not only achieves high efficiency and high power of the rotor supercharged gas turbine, but also realizes the functional gas energy generated by the rotor combustion chamber through structural improvements. The direct backward injection and jet splitting are beneficial to improving the propulsion efficiency of the rotor supercharged gas turbine. In addition, after the high-temperature and high-pressure power gas in the rotor combustion chamber is partially jetted and split to do power, the temperature of the remaining power gas in the combustion chamber will The corresponding reduction in pressure improves the working condition of the turbine blades in the turbine shell.

In the first gas pipeline side-mounted rotor supercharged gas turbine of the present invention, it includes a jet split rotor supercharged gas turbine, including a compressor and a turbine connected through a crankshaft. There are several rows of combustion chambers between the compressor and the turbine. The rotor of the chamber is installed in the rotor shell. The rotor shell is divided into a number of equal gas distribution angle zones, from the starting position in each gas distribution angle zone on the rotor shell to the end position along the rotor rotation direction. at the same angle, there are ventilation inlets and ventilation outlets at the same angle. After the ventilation inlet and ventilation outlet, an ignition chamber equipped with a spark plug, a first air outlet, a second air outlet, and a third air outlet are formed in sequence. The air outlet, the fourth air outlet and the fifth air outlet..., the air outlet of the compressor is connected to the ventilation inlet through the compressed air transmission pipe, and the ventilation outlet and the subsequent corresponding air outlet are connected to the ventilation inlet through the corresponding gas transmission pipe. The corresponding jets on the nozzle plate in front of the turbine are connected. After the first air outlet in each gas distribution angle zone is connected with the first gas pipe, the rear side of the first gas pipe extends backward from the periphery of the turbine shell. Through the turbine shell, the high-temperature and high-pressure working gas ejected from the first gas outlet can be ejected backward from the first gas pipeline, and the second gas outlet, third gas outlet, fourth gas outlet and The fifth air outlet... is connected to the corresponding jet openings on the nozzle plate in front of the turbine through corresponding respective gas delivery pipes.

When only the first gas transmission pipe in the jet-splitting rotor supercharged gas turbine is allowed to perform jet power, each first gas transmission pipe connected to the first gas outlet in each gas distribution angle zone extends backward through the turbine shell and then extends into the tail nozzle at the rear of the turbine housing, and connect the rear end of the first gas delivery pipe with the corresponding diffuser nozzle.

The rear side of the first gas transmission pipe can also be arranged in such a way that each first gas transmission pipe connected to the first gas outlet in each gas distribution angle area extends backward through the turbine shell, and the rear end of the first gas transmission pipe is connected to the tail nozzle The diffuser nozzles on the periphery of the tube are connected to Pass.

When blades are also provided on the rear side of the first gas delivery pipe, each first gas delivery pipe connected to the first air outlet in each gas distribution angle zone extends backward to the back of the turbine shell, and an air jet is formed at the rear end of the first gas delivery pipe. The last-stage blades installed on the rear side of the turbine are located outside the turbine shell. The blade tips of these final-stage blades are also connected to the connecting swivel ring, and the connecting swivel ring is located outside the turbine shell, connecting the front end surface of the swivel ring. The diameter size is the same as the diameter size of the rear end surface of the turbine shell. Double-acting outer ring blades are formed on the periphery of the connecting swivel ring. The jet port at the rear end of the first gas pipe is aligned with the outer ring blades connecting the periphery of the swivel ring. There is also a fan duct on the periphery of the ring blade. The fan duct is connected to the turbine shell through the guide column. The double-acting outer ring blade adopts a streamlined cross-section. The streamlined center line is basically a straight line with a thick arc. The windward and leeward sides of the shape extend from the front and back and gradually become slightly thinner. The high-temperature and high-pressure power gas ejected from the jet port at the rear end of the first gas pipe blows the outer ring blades, causing the outer ring blades to function as a turbine. After the outer ring blades rotate through the air outlet, the outer ring blades will pressurize the air flow entering from the front side of the fan duct and discharge it backward, allowing the outer ring blades to function as a fan again.

When the double-acting outer ring blades are made into a longer size, the corresponding air jets on the rear side of each first gas pipe also adopt an oblong shape and are inclined relative to the turbine axis. Arrange it so that one side of the long and flat air nozzle is far away from the axis center, and the long and flat air nozzle on the other side is close to the axis center. The width of the elongated air nozzle allows the air nozzle to correspond to multiple outer ring blades, and the elongated air nozzle can correspond to multiple outer ring blades. The radial size of the flat narrow portion is smaller than the radial length of the outer ring blades, so that the outer ring blades that rotate through the air jets can be continuously blown by the jetted airflow from the blade tips to the blade roots.

In the third embodiment of the jet split-flow rotor supercharged gas turbine, it includes a compressor and a turbine connected through a crankshaft. A rotor with several rows of combustion chambers is provided between the compressor and the turbine. The rotor is mounted on the rotor shell. Inside, the rotor shell is divided into several equal gas distribution angle zones. From the starting position in each gas distribution angle zone on the rotor shell to the end position along the direction of rotor rotation, there are successively located gas distribution angle zones within the same angle. The ventilation inlet and ventilation outlet, after the ventilation inlet and the ventilation outlet, form an ignition chamber equipped with a spark plug, a first air outlet, a second air outlet, a third air outlet, a fourth air outlet and a fifth air outlet in sequence. Air outlet..., the air outlet of the compressor is connected to the ventilation inlet through the compressed air pipe. The ventilation outlet and the corresponding air outlet behind it pass through the corresponding gas pipe and then connect to the corresponding jet on the nozzle plate before the turbine. Connected, the final blades located on the rear side of the turbine are located outside the turbine shell. The blade tips of these final blades are also connected to the peripheral connecting swivel ring, and the connecting swivel ring is located behind the turbine shell. The diameter size of the front end face of the connecting swivel ring is the same as the diameter size of the rear end face of the turbine. Peripheral outer ring blades are also formed on the connecting swivel ring. A flared turbine is provided on the periphery of the outer ring blades to cover the outer ring blades. The enlarged turbine shell is connected to the rear side of the turbine shell through the baffle ring. The first air outlet in each gas distribution angle zone and the two air outlets in the middle and last positions are directed along the periphery of the turbine shell through their respective air pipes. After extending rearward, a jet port is formed at the rear end of each gas delivery pipe. After the jet port at the rear end of the gas delivery pipe passes through the baffle ring between the expanded turbine shell and the turbine shell, it is aligned with the rear The outer ring blades on the surface, and the jet openings at the rear end of each gas pipe are wider, so that each jet opening can fill the annular jet opening arrangement space between the expanded turbine shell and the turbine shell, except for the first one in each gas distribution angle area. In addition to the air outlet and the two air outlets in the middle and last position, the remaining air outlets are connected to the corresponding jets on the nozzle plate before the turbine through corresponding respective air pipes.

In order to reduce the working temperature of the blades, cold air air pipes equipped with intercoolers are respectively led from each compressed air air pipe after the compressor, and the number of cold air air pipes is equal to the number of air distribution angle areas on the rotor shell. A cold air jet is also formed at the rear end of the cold air delivery pipe. After the cold air delivery pipes are evenly arranged among other air delivery pipes and pass through the baffle ring connecting the expanded turbine shell and the turbine shell, the cold air delivery pipes are The cold air jets at the rear end are aimed at the outer ring blades at the rear.

In order to allow the power of the turbine to be output, the final stage blades on the rear side of the turbine and the integrated outer ring blades can be installed on the rotor body of the turbine, or on a separate rotor disk on the power output shaft.

In the fourth embodiment of the jet split-flow rotor supercharged gas turbine, it includes a compressor and a turbine connected through a crankshaft. A rotor with several rows of combustion chambers is provided between the compressor and the turbine. The rotor is mounted on the rotor shell. Inside, the rotor shell is divided into several equal gas distribution angle zones. From the starting position in each gas distribution angle zone on the rotor shell to the end position along the direction of rotor rotation, there are successively located gas distribution angle zones within the same angle. The ventilation inlet and ventilation outlet, after the ventilation inlet and the ventilation outlet, form an ignition chamber equipped with a spark plug, a first air outlet, a second air outlet, a third air outlet, a fourth air outlet and a fifth air outlet in sequence. Air outlet..., the air outlet of the compressor is connected to the ventilation inlet through the compressed air pipe. The ventilation outlet and the corresponding air outlet behind it pass through the corresponding gas pipe and then connect to the corresponding jet on the nozzle plate before the turbine. Connected, the final blades located on the rear side of the turbine are located outside the turbine shell. The blade tips of these final blades are connected to the connecting swivel ring. The connecting swivel ring is located behind the turbine shell and connects the front end surface of the swivel ring. The diameter size is the same as the diameter size of the rear end face of the turbine shell. Peripheral outer ring blades are formed on the connecting swivel ring. A peripheral connecting outer ring is also formed on the blade tips of the outer ring blades. A peripheral connecting outer ring is also formed on the connecting outer ring. The fan blade is provided with a nozzle shell on the rear periphery of the turbine shell. The rear side of the turbine shell is connected to the rear side of the nozzle shell set on the periphery through a baffle ring. The diameter size of the rear end face of the nozzle shell is connected to the rear end face of the turbine shell with blades. The diameter of the front end face of the outer ring is the same. There is also a fan duct covering the fan blades on the periphery of the fan blades. The fan duct is connected to the nozzle shell on the periphery of the turbine shell through the guide column piece. In each air distribution angle area The first air outlet and the two air outlets in the middle and last positions extend rearward along the periphery of the turbine shell through their respective air pipes, and allow the jets formed at the rear ends of each air pipe to pass between the nozzle shell and the turbine shell The baffle ring is aligned with the outer ring blades at the back. The size of the jet ports at the rear end of each gas pipe is wider, so that each jet port can fill the annular jet port arrangement space between the nozzle shell and the turbine shell. In addition to the In addition to the first air outlet in the air angle area and the two air outlets in the middle and last positions, the remaining air outlets are connected to the corresponding jets on the nozzle plate before the turbine through their respective air pipes. The structure behind the turbine consisting of final stage blades, outer ring blades and fan blades is mounted on the turbine rotor body and the rear side through bearings. between the tail cones.

In order to cool the blades, cold air pipes equipped with intercoolers are also led from each compressed air pipe after the compressor, and the number of cold air pipes is equal to the number of air distribution angle areas on the rotor shell. These cold air pipes A cold air jet is also formed at the rear end. After the cold air pipes are evenly arranged between other gas pipes and pass through the baffle ring connecting the nozzle shell and the turbine shell, the cold air jets at the rear end of the cold air pipe are Aim at the rear outer ring blade.

In this improved jet split-flow rotor supercharged gas turbine, because the first gas transmission pipe is arranged in a side-by-side manner and extends backward, the high-temperature and high-pressure power gas generated in the rotor combustion chamber can be ejected directly backward. It improves the propulsion efficiency and is especially suitable as a power device for high-speed aircraft and large and medium-sized unmanned aerial vehicles. And let part of the power gas jet split, because the high-temperature and high-pressure power gas part is allowed to split to blow the outer ring blades that can be cooled, so that the remaining power gas with a corresponding decrease in temperature and pressure can drive the turbine operation and drive the compressor. Under the condition of improving working efficiency, the turbine blades do not need to be made of special high-temperature resistant materials, which will also reduce the manufacturing cost of turbine blades.

BRIEF DESCRIPTION OF THE DRAWINGS The jet split rotor supercharged gas turbine of the present invention will be described in detail below with reference to the accompanying drawings.

Figure 1 is a structural cross-sectional view of the jet split rotor supercharged gas turbine of the present invention.

Figure 2 is a cross-sectional view of the rotor shell and rotor of the jet split rotor supercharged gas turbine along line A-A in Figure 1 .

Figure 3 is a cross-sectional view of the tail nozzle of the jet-splitting rotor supercharged gas turbine along line B-B in Figure 1 .

Fig. 4 is a structural cross-sectional view of the jet-splitting rotor supercharged gas turbine according to the second embodiment of the present invention.

Figure 5 is a cross-sectional view of the tail structure of the jet split rotor supercharged gas turbine along line A-A in Figure 4 .

Figure 6 is a cross-sectional view of the double-acting blade taken along line B-B in Figure 4 .

Fig. 7 is a structural cross-sectional view of the jet split rotor supercharged gas turbine according to the third embodiment of the present invention.

Fig. 8 is a structural cross-sectional view of the jet split rotor supercharged gas turbine according to the fourth embodiment of the present invention.

Figure 9 is a cross-sectional view of the rear structure of the jet split rotor supercharged gas turbine along line A-A in Figure 8 .

DETAILED DESCRIPTION OF THE INVENTION The overall structure of the jet split rotor supercharged gas turbine of the present invention is shown in Figures 1 and 2, including a compressor 21 and a turbine 23 connected through a crankshaft 22. Between the compressor and the turbine there is a rotor 25 with several rows of combustion chambers 26, which is mounted in a rotor housing 29. The rotor shell 29 is divided into several equal gas distribution angle zones 40. As shown in Figure 2, the rotor shell 29 is divided into three equal gas distribution angle zones 40 (in high-power rotor supercharged gas turbines, also Four gas distribution angle zones can be set), each gas distribution angle zone occupies an angle area of 120 degrees. From the starting position in each gas distribution angle zone 40 on the rotor shell 29 to the end position where the rotor 25 rotates in the direction of arrow 56, there are ventilation inlets 8 and ventilation outlets 7 at the same angle. . After the ventilation inlet 8 and the ventilation outlet 7, an ignition chamber 31 equipped with a spark plug 30, a first air outlet 1, and The second air outlet 2, the third air outlet 3, the fourth air outlet 4 and the fifth air outlet 5..., the corresponding power gas outlets after the ventilation outlet 7 are connected to the front of the turbine through the corresponding gas pipes. The corresponding air jets on the nozzle plate 37 are connected.

In the connection between the air outlet end of the compressor and the ventilation inlet 8, as shown in Figure 1, the air outlet end of the compressor 21 is connected to the ventilation inlet 8 through the compressed air transmission pipe 9, and the ventilation outlet 7 is connected through the air transmission pipe 9. The air pipe 17 is connected with the air jet 7' on the jet plate 37. In Figure 1, the angle deflection is used to illustrate the state in which the combustion chamber 26 communicates with the ventilation inlet and the ventilation outlet when it is rotated to the positions of the ventilation inlet 8 and the ventilation outlet 7. At this time, the compressed air flowing out from the compressor 21 is Air is charged into the combustion chamber 26 through the compressed air pipe 9 and the ventilation inlet 8, squeezing out the medium-pressure working gas in the combustion chamber, completing the medium-pressure ventilation process in the combustion chamber, and the medium-pressure working gas discharged from the ventilation outlet 7 The power gas is then sprayed through the corresponding gas pipe 17 through the injection port 7' to the turbine 23 on the rear side. In practice, the compressed air air pipe 9 is also provided with a fuel nozzle (not shown) for forming a fuel mixture. In the three gas distribution angle areas 40 on the rotor shell 29 in the embodiment of Figure 2, after the ventilation inlet 8 and the ventilation outlet 7, an ignition chamber 31 equipped with a spark plug 30 and a first air outlet are arranged in sequence. 1. The second air outlet 2, the third air outlet 3, the fourth air outlet 4, the fifth air outlet 5 and the sixth air outlet 6, and the first air outlet 1 and the first output in each air distribution angle area 40 After the gas pipes 11 are connected, the rear side of the first gas pipe 24 extends backward from the periphery of the turbine shell 24 through the turbine shell, and then extends into the tail nozzle 19 at the rear of the turbine shell, and allows the rear side of the first gas pipe 11 to The end is connected with the corresponding expansion nozzle 20, so that the high-temperature and high-pressure working gas ejected from the first air outlet 1 can be ejected backward through the first gas pipe 11 and the expansion nozzle 20, so that it can be discharged from the first air outlet 1 Part of the work gas can directly produce jet force. The second air outlet 2, the third air outlet 3, the fourth air outlet 4, the fifth air outlet 5 and the sixth air outlet 6 after the first air outlet 1 are respectively connected through the corresponding air pipes 12 and 12. The gas pipe 13, the gas pipe 14, the gas pipe 15 and the gas pipe 16 are connected with each corresponding jet port on the nozzle plate 37, so that the temperature and pressure of the functional gas energy can be reduced accordingly, the second gas outlet 2 and the subsequent gas outlets are sequentially The decompressed gas is sprayed outward, and then sprayed from the corresponding jets on the nozzle plate 37 to the turbine 23 through the corresponding gas pipes, driving the turbine to rotate and perform work. While the turbine 23 rotates and performs work, it also drives the compressor 21 to continue to generate compression. Air.

In practice, by increasing or decreasing the flow cross section of the first gas outlet 1, the amount of working gas entering the first gas pipe 11 can be increased or reduced, and thus the high-pressure gas direct injection propulsion force and the turbojet propulsion force can also be determined. size ratio between. Under the condition that the turbine 23 can drive the compressor 21, the first air outlet 1 should be allowed to eject more power gas as much as possible to increase the driving force generated by the direct injection of high-pressure power gas.

In practice, each first gas pipe 11 connected to the first gas outlet 1 in each gas distribution angle area 40 can also be allowed to extend backward through the turbine shell 24 without extending into the tail nozzle 19, but to allow the first gas pipe 11 to extend backward through the turbine shell 24. The rear end of the gas pipe is connected to the diffuser nozzle 20 attached to the periphery of the tail nozzle 19 (not shown).

In order to reduce the heat loss generated when the power gas flows through the first gas pipeline 11 , at least a heat insulation layer 41 should be provided on the first gas pipeline 11 . In addition, in practice, it can also be provided in the diffusion nozzle 17 at the rear end of the first gas pipe 11 The corresponding afterburner injector can flexibly increase the jet force.

When this type of jet-splitting rotor supercharged gas turbine is used as aircraft power, part of the work gas in the combustion chamber can be directly injected backwards and generate greater back-injection driving force, which not only improves the work of the rotor supercharged gas turbine. efficiency, and the remaining power gas with correspondingly lower temperature and pressure is used to drive the turbine operation, which also reduces the operating temperature of the turbine blades and improves the operating conditions of the turbine blades. There is no need to use particularly high-temperature resistant materials to manufacture the turbine blades.

In the second embodiment of the present invention as shown in Figure 4, in order to convert the working gas ejected backward from the first gas pipe 11 into a greater forward driving force, the gas pipe 11 is installed behind the first gas pipe 11. Double-acting outer ring blades are installed behind the side jets. This embodiment is shown in Figure 4. In each gas distribution angle area 40 of the rotor shell 29 (see Figure 2), each first gas transmission pipe 11 connected with the first air outlet 1 in each gas distribution angle area 40 is rearward. After extending to the turbine housing 24 , an injection port 38 is formed at the rear end of the first gas pipe 11 . The last-stage blades 42 provided on the rear side of the turbine 23 are located outside the turbine shell 24. The blade tips of these final-stage blades 42 are also connected to the connecting swivel 39, and the connecting swivel is located at the outer side of the turbine shell 24. outside. The diameter size of the front end face of the connecting swivel is the same as the diameter size of the rear end face of the turbine shell 24, which is equivalent to the continuation of the rear end of the turbine shell 24 to the rear tail nozzle. Double-acting outer ring blades are also formed on the periphery of the connecting swivel 39. 36. The air jet 38 at the rear end of the first gas pipe 11 is aligned with the outer ring blades 36 connected to the periphery of the rotating ring 39 . After the combustion chamber 26 on the rotor 25 is connected to the first gas outlet 1 on the rotor shell 29, the work gas with the highest temperature and pressure in the combustion chamber will first be ejected from the first gas outlet to the outer part, and pass through the first gas outlet. The air jet 38 at the rear end of the gas pipe blows the outer ring blades 36, so that when the double-acting outer ring blades rotate, they can produce greater forward thrust like a fan. A fan duct 43 is also provided around the outer ring blades. , the fan duct is connected to the turbine shell 24 through the guide column piece 45.

The double-acting outer ring blade 36 behind the jet port 38 adopts a streamlined cross-section (see Figure 6). The streamlined centerline 51 is basically a straight line, and the outer ring blade located on the periphery of the connecting swivel 39 has a thicker arc shape. The front face 52 and the windward face 53 and the leeward face 54 extend rearwardly and gradually become slightly thinner. Of course, in order to allow the outer ring blades at different radii to exhaust air evenly backwards, the windward angle of the outer ring blades will be twisted accordingly from the blade root to the blade tip. This double-acting outer ring blade 36 is blown by the power gas energy and interacts with the air flow as shown in Figure 6. The high-temperature and high-pressure power gas ejected from the jet port 38 at the rear end of the first gas pipe blows along the arrow 58. Moving the outer ring blades 36 causes the outer ring blades to receive a rotational force as indicated by arrow 57, allowing the double-acting outer ring blades 36 to function as turbines. After the outer ring blades rotate through the air outlet 38, the outer ring blades will pressurize the air flow entering from the front side of the fan duct 43 and discharge it backward in the direction shown by arrow 59, allowing the double-acting outer ring blades 36 to start again. to the fan function, thereby increasing the forward thrust of the gas turbine. Of course, the cross-sectional shape of the double-acting blade 32 is not a very good turbine blade shape, nor is it a very good fan blade shape. It can only be a compromise between being used for power gas blowing work and being used as a fan to exhaust air backward.

In practice, when the double-acting outer ring blade 36 is made into a longer size, as shown in Figure 5, the corresponding first The ejection port 38 on the rear side of the gas pipe 11 also adopts an elongated and oblong shape, and is arranged obliquely relative to the axis of the turbine, so that one side of the elongated elongated ejection port is far away from the axis center, and the elongated elongated ejection port on the other side is close to the axis center. The size of the width of the air outlet 38 allows the air outlet to correspond to multiple outer ring blades 36, so that the air flow ejected from the air outlet 38 can blow onto multiple double-acting outer ring blades 36 at the same time. The radial size of the flat and narrow part of the nozzle 38 is smaller than the length of the outer ring blade 36 in the radial direction, so that the air flow ejected from the nozzle 38 can only blow on part of the area of the double-action blade. The obliquely arranged nozzle 38 It also enables the outer ring blades that rotate through the air jets to be continuously blown by the ejected airflow from the tip of the blade to the root of the blade, so that the blown double-action blade will not be subject to too much impact force of the working gas. Since three gas distribution angle zones 40 are provided on the rotor shell 29 (see Figure 2), the air jets 38 on the rear side of the first gas delivery pipe 11 in each gas distribution angle zone extend to the rear double-acting outer ring blades. 36, as shown in Figure 5, there will be three air jets 38 spaced 120 degrees apart and aligned with the double-acting outer ring blades.

If the double-acting outer ring blades 36 are shorter in size, the radial size of the air jets 38 at the rear of each first gas pipe 11 can be basically the same as the radial length of the double-acting outer ring blades 36 (not shown).

In the rotor supercharged gas turbine of the second embodiment shown in FIG. 4 , although the highest temperature working gas flow is ejected from the injection port 38 , the double-acting outer ring blades 36 are blown by the high-temperature air flow and then merge with the front ones. The incoming cold air interacts with each other and is cooled, so that the operating temperature of the double-acting outer ring blades will not be very high, and there is no need to use additional cooling for the blades.

The third embodiment of the jet split rotor supercharged gas turbine is shown in Figure 7. The compressor 21, rotor shell 29 and rotor 25 of the gas turbine are basically the same as those in the first and second embodiments, including the compressor 21 and the compressor 21 connected through the crankshaft. The turbine 23 is provided with a rotor 25 with several rows of combustion chambers 26 between the compressor and the turbine. The rotor is installed in the rotor shell 29, and the rotor shell 29 is divided into a number of equal gas distribution angle zones 40 (see figure 2), from the starting position in each gas distribution angle zone 40 on the rotor shell 29 to the end position along the rotation direction of the rotor 25, there are ventilation inlets 8 and ventilation outlets 7 at the same angle. , after the ventilation inlet and the ventilation outlet, an ignition chamber 31 equipped with a spark plug 30, a first air outlet 1, a second air outlet 2, a third air outlet 3, a fourth air outlet 4 and a fifth air outlet are formed in sequence. 5..., the ventilation outlet 7 and the corresponding air outlets thereafter are connected to the corresponding jet ports on the nozzle plate 37 in front of the turbine through corresponding gas pipes.

Compared with the first embodiment, the difference of the third embodiment is that in addition to the separately arranged first gas pipeline 11, other corresponding gas pipelines are also separately arranged on the rotor shell 29, and these separately arranged The gas pipe uses the air jet on its rear side to blow the additional outer ring blades. These separately arranged gas transmission pipes and the provided outer ring blades are shown in Figure 7. The final stage blades 42 provided on the rear side of the turbine 23 are located outside the turbine shell 24. The blades of these final stage blades 42 The top is also connected to the peripheral connecting swivel 39, and the connecting swivel is located behind the turbine shell 24. The diameter of the front end face of the connecting swivel is the same as the diameter of the rear end face of the turbine shell 24, which is equivalent to the rear end of the turbine shell 24. Continuation of the tail nozzle toward the rear. A peripheral outer ring blade 32 is also formed on the connecting swivel 39. A flared turbine shell 27 is provided on the periphery of the ring blades, which covers the outer ring blades. The flared turbine shell is connected to the rear side of the turbine shell 24 via a baffle ring 28 .

After the outer ring blades 32 are formed on the final stage blades 42 through the connecting swivel 39, the first air outlet 1 in each valve angle area 40 and the two air outlets at the middle and last positions are passed along the turbine through their respective air pipes. The outer periphery of the shell 24 extends backward, and an air jet 38 is formed at the rear end of each gas pipeline. The jet port at the rear end of the gas pipeline passes through the baffle ring 28 between the expanded turbine shell 27 and the turbine shell 24, and then is aligned. The outer ring blade 32 at the rear. If the third embodiment in Figure 7 adopts the same rotor shell structure as the first and second embodiments, the rotor shell is divided into three valve angle zones 40 (see Figure 2), and each of the rotor shells 29 is The first to sixth air outlets are provided in a gas distribution angle area 40. The first air outlet 1 passes through the first air pipe 11 and uses the jet port 38 at the rear end of the air pipe to pass through the gap between the flared turbine shell and the turbine shell. After the baffle ring 28 is aligned with the outer ring blade 32 at the rear, the air delivery pipes of the two air outlets in the middle and last positions are also arranged separately outward, that is, the fourth air outlet 4 (or the third air outlet 3) The gas delivery pipe 14 and the gas delivery pipe 16 of the sixth air outlet 6 are also arranged outwardly separately, and the corresponding air jets 38 on the rear side of the two gas delivery pipes pass through the baffle ring 28 and are aligned with the rear outer ring blades 32. In order to enable each jet port to fill the annular jet port arrangement space between the expanded turbine shell 27 and the turbine shell 24, each jet port 38 at the rear end of each gas delivery pipe is formed in a wider size.

In the corresponding air pipe arrangement of each air outlet on the rotor shell 29, in addition to the first air outlet 1 in each air distribution angle zone 40 and the two air outlets in the middle and last positions, each air distribution angle on the rotor shell 29 The remaining air outlets in the zone 40 are respectively connected to the corresponding jets on the nozzle plate 37 in front of the turbine 23 through corresponding air pipes.

In the third embodiment of Figure 7, since the corresponding air pipes of the first air outlet, the fourth air outlet and the sixth air outlet are arranged separately (see Figure 2 for the arrangement of each air outlet), the rotor shell 29 is equipped with The remaining second air outlet 2, third air outlet 3 and fifth air outlet in the air angle area 40 will be connected to the corresponding air jets on the nozzle plate 37 in front of the turbine 23 through corresponding air pipes. In Figure 7, through the deflection angle, it is depicted that when the combustion chamber 26 on the rotor is rotated to the position of the ventilation inlet 8 and the ventilation outlet 7, the ventilation inlet and the ventilation outlet are communicated, and medium-pressure ventilation is performed in the combustion chamber. In the process, the ventilation outlet 7 leads to the corresponding air jet on the nozzle plate 37 through the gas pipe 17.

In a general gas turbine, the higher the temperature in front of the turbine, the higher the efficiency of the gas turbine. However, the turbine blades are required to withstand the higher temperature of the power gas, which increases the manufacturing cost of the turbine blades. In the jet-splitting rotor supercharged gas turbine of the third embodiment in Figure 7, since the highest-temperature power gas has been ejected from the first gas outlet, the temperature of the power gas flowing out from the other gas outlets has been relatively reduced, correspondingly The operating temperature of the turbine blades is reduced and the turbine operating conditions are improved.

Since the high-temperature power gas sprayed from the first air outlet will also cause the blown blades to withstand high gas temperatures, in order to avoid overheating of the outer ring blades, as shown in Figure 7, the gas after the compressor 21 can also be Each compressed air pipe 9 can also lead to a cold air pipe 48 provided with an intercooler 49, and at the same time, the number of cold air pipes and the rotor The number of air distribution angle zones 40 on the shell is the same. Cold air jets 50 are formed at the rear ends of these cold air air pipes. The cold air air pipes 48 are evenly arranged between other air pipes and connected through the expanded turbine shell. 27 and the baffle ring 28 of the turbine shell 24, then align the cold air jet at the rear end of the cold air pipe with the outer ring blades 32 at the back, and use the cooled compressed air to blow and cool the outer ring blades 32, so that the outer ring The temperature of the blades will not rise particularly, and the turbine blades do not need to be made of special high-temperature resistant materials.

In practice, the final blade 42 on the rear side of the turbine 23 and the integrated outer ring blade 32 can be installed on the rotor body 33 of the turbine 23, or as shown in Figure 7, the final blade 42 on the rear side of the turbine 23 can be installed on the rotor body 33 of the turbine 23. 42 and the integrated outer ring blades 32 are installed on a separate rotor disk 34 on the power output shaft 35, allowing this rotor supercharged gas turbine to output power outward through the power output shaft 35. Of course, in order to allow the outer ring blades 32 to generate greater power, the connecting swivel 39 can also be lengthened backwards, and another level of outer ring blades (not shown) can be provided behind the outer ring blades 32 . Since the jet split rotor supercharged gas turbine in the embodiment of FIG. 7 mainly outputs power through the power output shaft 35, it can be used as a power device for propeller aircraft, helicopters, vehicles, ships and power stations.

The fourth embodiment of the jet split rotor supercharged gas turbine is shown in Figure 8. Its basic structure is the same as that of the first, second and third embodiments, and also includes a compressor 21 and a turbine 23 connected through a crankshaft 22. . Between the compressor and the turbine there is a rotor 25 with several rows of combustion chambers 26, which is mounted in a rotor housing 29. The rotor shell 29 is divided into a number of equal gas distribution angle zones 40 (see Figure 2). From the starting position in each gas distribution angle zone 40 on the rotor shell 29 to the end position along the rotation direction of the rotor 25, A ventilation inlet 8 and a ventilation outlet 7 are provided at the same angle in sequence. After the ventilation inlet and the ventilation outlet, an ignition chamber 31 equipped with a spark plug 30, a first air outlet 1, and a second air outlet are formed in sequence. 2. The third air outlet 3, the fourth air outlet 4 and the fifth air outlet 5..., the ventilation outlet 7 and the corresponding air outlets thereafter pass through the corresponding gas pipes and then connect to the corresponding nozzle plate 37 in front of the turbine. The jets are connected. In the fourth embodiment of Fig. 8, the structure of the rotor shell 29 can also be the same as that of the first embodiment (see Fig. 2). Three gas distribution angle zones 40 are provided on the rotor shell (the high-power model can be provided with four gas distribution angle area), and a first air outlet 1, a second air outlet 2, a third air outlet 3, a fourth air outlet 4, a fifth air outlet 5 and a sixth air outlet are provided in each air distribution angle area 6. Six air outlets are set up.

The jet split-rotor supercharged gas turbine of the fourth embodiment is mainly used as a power device for a jet aircraft. As shown in Figure 8, the final blades 42 provided on the rear side of the turbine 23 are located outside the turbine casing 24. The tip of the stage blade 42 is connected to the connecting swivel ring 39. The connecting swivel ring is located behind the turbine shell 24, and the diameter of the front end face of the connecting swivel ring is the same as the diameter of the rear end face of the turbine shell 24, which is equivalent to the diameter of the rear end face of the turbine shell 24. The continuation of the tail nozzle from the end to the rear. A peripheral outer ring blade 32 is also formed on the connecting rotating ring 39, a peripheral connecting outer ring 41 is formed on the blade tip of the outer ring blade 32, and a fan blade 44 is also formed on the connecting outer ring.

A nozzle shell 46 is provided on the rear periphery of the turbine shell 24. The rear side of the turbine shell 24 is connected to the rear side of the nozzle shell 46 provided on the periphery through the baffle ring 28. The diameter size of the rear end surface of the nozzle shell 46 is consistent with the rear end face of the nozzle shell 46. connecting outer ring of blade The diameter of the front end face of 41 is the same, which is equivalent to the continuation of the rear end of the nozzle shell 46 to the rear through the connecting outer ring 41. There is also a fan duct 43 that covers the fan blades on the periphery of the fan blade 44. The fan duct is connected to the nozzle shell 46 on the periphery of the turbine shell 24 through the guide column 45, so that the jet split rotor with this structure can increase the The pressure gas turbine becomes a fan-ducted rear-mounted jet engine.

In the arrangement of the gas delivery pipes of the air outlets on the rotor shell 29, the first air outlet 1 in each gas distribution angle zone 40 and the two air outlets at the middle and last positions are respectively passed through their respective gas delivery pipes and rearward along the periphery of the turbine shell 24. Extend, and allow the jet ports 38 formed at the rear ends of each gas delivery pipe to pass through the baffle ring 28 between the jet housing 46 and the turbine housing 24 to align with the rear outer ring blades 32 . The size of the air jets at the rear end of each gas pipe is relatively wide, as shown in FIG. 9 , so that each air jet 38 can fill the annular air jet arrangement space between the nozzle housing 46 and the turbine housing 24 . In addition to the first air outlet 1 and the two air outlets in the middle and last positions in each valve angle area 40, the remaining air outlets pass through the corresponding air pipes and the nozzle plate 37 in front of the turbine 23. The corresponding jets are connected.

In the connection layout of each air outlet (see Figure 2) on the rotor shell 29 and each gas delivery pipe, the separately arranged first air outlet 1 leads to the baffle ring 28 between the nozzle shell and the turbine shell through the gas delivery pipe 11, And let the jet port 38 at the rear end of the gas pipe be aligned with the outer ring blade 32 at the back. After the first air outlet, as shown in Figure 9, the corresponding air pipes 14 and 16 of the fourth air outlet and the sixth air outlet in the middle and last position can be allowed to lead to the baffle ring 28, so that the temperature and pressure are relatively high. The high power gas pushes the outer ring blades 32 and drives the fan blades 44 on the periphery of the outer ring blades, allowing this part of the power gas to generate greater forward thrust through the fan blades. The corresponding gas delivery pipes 12, 13 and 15 of the remaining second air outlet 2, third air outlet 3 and fifth air outlet 5 in each air distribution angle zone 40 on the rotor shell will be connected with those in front of the turbine 23. The corresponding jets on the nozzle plate 37 are connected to each other, allowing the work gas with a correspondingly lower temperature to push the turbine 23 in the turbine shell 24 to rotate and work, thereby improving the operating conditions of the turbine.

Since the rotational speed of the fan blades is relatively low, the structure behind the turbine 23 consisting of the final blade 42, the outer ring blade 32 and the fan blade 44 is installed between the rotor body 33 of the turbine and the rear tail cone 47 through bearings. .

Since the high-temperature power gas sprayed from the first air outlet has a very high temperature, in order to prevent the outer ring blades from overheating, as shown in Figure 8, each compressed air pipe 9 after the compressor 21 is also provided with an intercooler. The cold air delivery pipe 48 of 49 and the intercooler 49 are installed in the cooler shell 60. The cold air enters from the air inlet 61 on the cooler shell and takes away the compression heat of the compressed air flowing through the intercooler 49 and then from The air flows out from the air outlet 62 on the cooler shell. The number of cold air delivery pipes 48 connected from the intercooler 49 is the same as the number of air distribution angle areas 40 on the rotor shell. Cold air jets 50 are also formed at the rear ends of these cold air delivery pipes, so that the cold air delivery pipes 48 are evenly arranged on the After the other air pipes pass through the baffle ring 28 connecting the nozzle shell 46 and the turbine shell 24, the cold air jets 50 at the rear end of the cold air air pipes are aligned with the outer ring blades 32 at the rear. The positions of the cold air jets 50 at the rear end of each cold air pipe are shown in Figure 9 and are respectively located behind the gas pipe 16 so that the outer ring blades 32 blown by the high-temperature power gas will not be overheated.

Claims

A jet split-flow rotor supercharged gas turbine includes a compressor (21) and a turbine (23) connected through a crankshaft. A rotor (25) with several rows of combustion chambers (26) is provided between the compressor and the turbine. The rotor is installed in the rotor shell (29). The rotor shell (29) is divided into a number of equal gas distribution angle zones (40). From the starting point of each gas distribution angle zone (40) on the rotor shell (29) position, to the end position along the rotation direction of the rotor (25), there are ventilation inlets (8) and ventilation outlets (7) at the same angle. After the ventilation inlet and the ventilation outlet, a ventilation inlet (8) and a ventilation outlet (7) are formed in sequence. The ignition chamber (31) equipped with the spark plug (30), the first air outlet (1), the second air outlet (2), the third air outlet (3), the fourth air outlet (4) and the fifth air outlet ( 5)..., the air outlet of the compressor (21) is connected to the ventilation inlet (8) through the compressed air pipe (9), and the ventilation outlet (7) and the subsequent corresponding air outlet are connected through the corresponding gas pipes. Then it is connected with the corresponding jet port on the nozzle plate (37) before the turbine, which is characterized in that: the first air outlet (1) in each gas distribution angle zone (40) is connected with the first gas pipe (11) Finally, the rear side of the first gas pipe extends backward through the turbine shell from the periphery of the turbine shell (24), so that the high-temperature and high-pressure working gas ejected from the first gas outlet (1) can be sprayed backward from the first gas pipe. out, the second air outlet (2), the third air outlet (3), the fourth air outlet (4) and the fifth air outlet (5)... after the first air outlet (1) are passed through the corresponding Each gas delivery pipe is connected with each corresponding jet port on the nozzle plate (37) before the turbine (23).
The jet split rotor supercharged gas turbine according to claim 1, characterized in that: each first gas transmission pipe (11) connected to the first gas outlet (1) in each gas distribution angle zone (40) extends backward through After the turbine shell (24), it extends into the tail nozzle (19) at the rear of the turbine shell, and connects the rear end of the first gas delivery pipe (11) with the corresponding expansion nozzle (20).
The jet split rotor supercharged gas turbine according to claim 1, characterized in that: each first gas transmission pipe (11) connected to the first gas outlet (1) in each gas distribution angle zone (40) extends backward through Behind the turbine shell (24), the rear end of the first gas pipe is connected to the expansion nozzle (20) attached to the periphery of the tail nozzle (19).
The jet split rotor supercharged gas turbine according to claim 1, characterized in that: each first gas transmission pipe (11) connected to the first gas outlet (1) in each gas distribution angle zone (40) extends backward to Behind the turbine shell (24), a jet opening (38) is formed at the rear end of the first gas pipe (11), and the final blade (42) provided on the rear side of the turbine (23) is located at the center of the turbine shell (24). At the outer position, the blade tips of these final blades (42) are also connected to the connecting swivel (39), and the connecting swivel is located outside the turbine shell (24). The diameter of the front end face of the connecting swivel is in line with the turbine shell (24). 24) The diameters of the rear end faces are the same, and double-acting outer ring blades (36) are formed on the periphery of the connecting swivel (39). The jet port (38) at the rear end of the first gas pipe (11) is aligned with the connecting swivel. (39) The outer ring blades (36) are also provided with a fan duct (43) on the periphery of the outer ring blades. The fan duct is connected to the turbine shell (24) through the guide column piece (45). The double-acting The outer ring blades (36) adopt a streamlined cross-section and a streamlined center line (51) It is basically a straight line, with a thicker arc front (52) and a windward side (53) and a leeward side (54) that extend backward and gradually become slightly thinner, starting from the jet outlet (38) at the rear end of the first gas pipe The ejected high-temperature and high-pressure power gas blows the outer ring blades (36), causing the outer ring blades to function as turbines. After the outer ring blades rotate through the air jets, the outer ring blades turn the air from the front of the fan duct (43) The air flow entering from the side is pressurized and discharged backward, allowing the outer ring blades to function as a fan again.
The jet split rotor supercharged gas turbine according to claim 4, characterized in that when the double-acting outer ring blades (36) are made into a longer size, the corresponding jets on the rear side of each first gas pipe (11) The port (38) also adopts an elongated shape and is arranged obliquely relative to the axis of the turbine, so that one side of the elongated elongated nozzle is far away from the axis, and the elongated elongated nozzle on the other side is close to the axis. The elongated elongated nozzle ( The width of 38) allows the jet port to correspond to multiple outer ring blades (36), and the radial size of the narrow flat part of the jet port (38) is smaller than the length of the outer ring blade (36) in the radial direction, making it easier to rotate. The outer ring blades of the air jet (38) can be continuously blown by the jetted airflow from the blade tip to the blade root.
A jet split-flow rotor supercharged gas turbine includes a compressor (21) and a turbine (23) connected through a crankshaft. A rotor (25) with several rows of combustion chambers (26) is provided between the compressor and the turbine. The rotor is installed in the rotor shell (29). The rotor shell (29) is divided into a number of equal gas distribution angle zones (40). From the starting point of each gas distribution angle zone (40) on the rotor shell (29) position, to the end position along the rotation direction of the rotor (25), there are ventilation inlets (8) and ventilation outlets (7) at the same angle. After the ventilation inlet and the ventilation outlet, a ventilation inlet (8) and a ventilation outlet (7) are formed in sequence. The ignition chamber (31) equipped with the spark plug (30), the first air outlet (1), the second air outlet (2), the third air outlet (3), the fourth air outlet (4) and the fifth air outlet ( 5)..., the air outlet of the compressor (21) is connected to the ventilation inlet (8) through the compressed air pipe (9), and the ventilation outlet (7) and the subsequent corresponding air outlet are connected through the corresponding gas pipes. It is then connected to the corresponding jet port on the nozzle plate (37) in front of the turbine, and is characterized in that the final stage blade (42) provided on the rear side of the turbine (23) is located outside the turbine shell (24). The blade tips of these final blades (42) are also connected to the peripheral connecting swivel (39), and the connecting swivel is located behind the turbine shell (24). The diameter of the front end face of the connecting swivel is in line with the turbine shell (24). ) have the same diameter size on the rear end face, and peripheral outer ring blades (32) are also formed on the connecting swivel (39). A flared turbine shell (27) is provided on the periphery of the outer ring blades to cover the outer ring blades. ), the flared turbine shell is connected to the rear side of the turbine shell (24) through the baffle ring (28), the first air outlet (1) in each valve angle area (40) and the two outlets at the middle and last positions The gas ports respectively extend backward along the periphery of the turbine shell (24) through respective gas delivery pipes, and a jet port (38) is formed at the rear end of each gas delivery pipe. The jet port at the rear end of the gas delivery pipe passes through the flared turbine shell (27) and the turbine shell. The baffle ring (28) between (24) is then aligned with the rear outer ring blade (32). The size of the jet opening at the rear end of each air pipe is wider, so that each jet opening (38) can be filled with the expanded turbine. The annular air jet arrangement space between the shell (27) and the turbine shell (24), in addition to the first air outlet (1) in each valve angle area (40) and the two air outlets in the middle and last position, The remaining air outlets are respectively connected to the corresponding jet ports on the nozzle plate (37) in front of the turbine (23) through the corresponding air pipes.
The jet split-flow rotor supercharged gas turbine according to claim 6, characterized in that: cold air transmission pipes (9) equipped with intercoolers (49) are respectively led out from each compressed air transmission pipe (9) after the compressor (21). The air pipe (48), and the number of the cold air air pipes is the same as the number of the air distribution angle areas (40) on the rotor shell. Cold air jets (50) are also formed at the rear ends of these cold air air pipes, and the cold air air pipes (48) are Evenly distributed between the other gas delivery pipes and passing through the baffle ring (28) connecting the expanded turbine shell (27) and the turbine shell (24), then let the cold air jet port (50) at the rear end of the cold air delivery pipe Aim at the rear outer ring blade (32).
The jet split rotor supercharged gas turbine according to claim 6 or 7, characterized in that: the final stage blade (42) on the rear side of the turbine (23) and the integrated outer ring blade (32) can be installed on the turbine The rotor body (33) of (23) can be mounted on the independent rotor disk (34) on the power output shaft (35).
A jet split-flow rotor supercharged gas turbine includes a compressor (21) and a turbine (23) connected through a crankshaft. A rotor (25) with several rows of combustion chambers (26) is provided between the compressor and the turbine. The rotor is installed in the rotor shell (29). The rotor shell (29) is divided into a number of equal gas distribution angle zones (40). From the starting point of each gas distribution angle zone (40) on the rotor shell (29) position, to the end position along the rotation direction of the rotor (25), there are ventilation inlets (8) and ventilation outlets (7) at the same angle. After the ventilation inlet and the ventilation outlet, a ventilation inlet (8) and a ventilation outlet (7) are formed in sequence. The ignition chamber (31) equipped with the spark plug (30), the first air outlet (1), the second air outlet (2), the third air outlet (3), the fourth air outlet (4) and the fifth air outlet ( 5)..., the air outlet of the compressor (21) is connected to the ventilation inlet (8) through the compressed air pipe (9), and the ventilation outlet (7) and the subsequent corresponding air outlet are connected through the corresponding gas pipes. Then it is connected with the corresponding jet port on the nozzle plate (37) before the turbine, which is characterized in that the final stage blade (42) provided on the rear side of the turbine (23) is located outside the turbine shell (24). The tip of the final blade (42) is connected to the connecting swivel (39). The connecting swivel is located behind the turbine shell (24), and the diameter of the front end face of the connecting swivel is equal to the diameter of the rear end face of the turbine shell (24). The dimensions are the same, a peripheral outer ring blade (32) is formed on the connecting swivel (39), a peripheral connecting outer ring (41) is also formed on the blade tip of the outer ring blade (32), and a peripheral connecting outer ring (41) is also formed on the connecting outer ring. A fan blade (44) is formed, and a nozzle housing (46) is provided on the rear periphery of the turbine housing (24). The rear side of the turbine housing (24) is connected to the nozzle housing (46) provided on the periphery through a baffle ring (28). ) are connected to the rear side. The diameter of the rear end surface of the nozzle shell (46) is the same as the diameter of the front end surface of the connecting outer ring (41) with blades at the back. There is also a fan blade cover on the periphery of the fan blade (44). There is a fan duct (43) in it. The fan duct is connected to the nozzle shell (46) on the periphery of the turbine shell (24) through the guide column piece (45). 1) and the two air outlets at the middle and last positions respectively extend backward along the periphery of the turbine shell (24) through their respective air pipes, and let the jets (38) formed at the rear ends of each air pipes pass through the nozzle housing (46 ) and the turbine shell (24), and then align it with the outer ring blades (32) at the back. The size of the jet openings at the rear end of each air pipe is wider, so that each jet opening (38) can discharge air. The annular jet arrangement space between the full jet housing (46) and the turbine housing (24), except for the first air outlet (1) in each valve angle area (40) and one of the two air outlets in the middle and last position In addition, the remaining air outlets are connected to the corresponding jet ports on the nozzle plate (37) in front of the turbine (23) through the corresponding air pipes. The ones behind the turbine (23) are connected by the final blade (42), The structure composed of outer ring blades (32) and fan blades (44) is installed between the turbine rotor body (33) and the rear tail cone (47) through bearings.
The jet-splitting rotor supercharged gas turbine according to claim 9, characterized in that: cold air transmission pipes equipped with intercoolers (49) are respectively led from each compressed air gas transmission pipe (9) after the compressor (21). The air pipe (48), and the number of the cold air air pipes is the same as the number of the air distribution angle areas (40) on the rotor shell. Cold air jets (50) are also formed at the rear ends of these cold air air pipes, and the cold air air pipes (48) are After evenly distributing between the other air pipes and passing through the baffle ring (28) connecting the nozzle shell (46) and the turbine shell (24), align the cold air jets (50) at the rear end of the cold air pipes. At the back of the outer ring blade (32).