Multi-layer gas-spray-cylinder-type rotor-boosted gas turbine

Abstract

A multi-layer gas-spray-cylinder-type rotor-boosted gas turbine, comprising a gas compressor, a rotor and a turbine, wherein an inner-ring gas spray cylinder (21) is provided in front of the turbine (8), and each first gas pipe (11) is in communication with the inner-ring gas spray cylinder; first-stage blades (61) of the turbine are located on the rear side of the inner-ring gas spray cylinder; a second-stage gas spray cylinder (31) is provided at the periphery of the inner-ring gas spray cylinder; each second gas pipe (12) is in communication with the second-stage gas spray cylinder; second-stage blades (62) of the turbine are located on the rear side of the second-stage gas spray cylinder; in the same manner, a third-stage gas spray cylinder and a fourth-stage gas spray cylinder are further provided until corresponding gas pipes connected to a rotor housing are all sequentially in communication with the gas spray cylinders capable of blowing the blades of the turbine, such that working gases having different pressures are enabled to blow the corresponding different blades on the turbine by means of different gas spray cylinders, thereby preventing pulsation damage caused to the blades of the turbine by the working gases, which have different pressures, and enabling the turbine to operate stably and efficiently.

Description

Multi-layer gas nozzle rotor supercharged gas turbine

[0001] FIELD OF THE INVENTION The present invention relates to a rotor-supercharged gas turbine, and in particular to a multi-layer gas nozzle-type rotor-supercharged gas turbine.

[0002] Background Art In the rotor-supercharged gas turbine with application number 202010650212.X and the jet-split rotor-supercharged gas turbine with return piping with application number 202211678864.X, although the working gas can be sequentially ejected into the turbine through different gas outlets on the casing and corresponding gas pipes, the working gas within adjacent gas pipes has a certain pressure difference, which causes the turbine blades to be subject to certain working gas pressure pulsations. This is not conducive to the stable operation of the turbine blades and can easily damage the turbine blades. In the jet-split rotor-supercharged gas turbine with return piping, although the splitting of the working gas can relatively reduce the effect of the working gas pressure pulsation on the turbine blades, it still cannot eliminate the working gas pressure pulsation on the turbine blades.

[0003] SUMMARY OF THE INVENTION The present invention aims to provide a multi-layered gas-injection rotor-supercharged gas turbine. Through structural improvements, this not only prevents the pulsation of working gases of varying pressure on the turbine blades, but also allows the working gases to generate greater turbine output power, thereby improving the efficiency of the gas turbine. By incorporating a single-injection power turbine, the present invention further optimizes and improves the operating conditions of the turbine blades.

[0004] This multi-layer gas nozzle rotor supercharged gas turbine includes a compressor, a rotor connected by a shaft, and a turbine. The rotor is installed in a rotor shell, and a plurality of rows of combustion chambers are provided on the rotor. The rotor shell is divided into a plurality of equal valve timing angle zones. From the starting position of each valve timing angle zone on the rotor shell to the end position along the direction of rotation of the rotor, there are ventilation inlet holes and ventilation outlet holes at the same angle in sequence. The outlet end of the compressor is connected to the ventilation inlet hole on the rotor shell through a compressed air pipe. The ventilation outlet hole is connected to the turbine on the rear side through a corresponding air supply pipe. After the ventilation inlet hole and the ventilation outlet hole, an ignition chamber equipped with a spark plug, a first outlet hole, and a second outlet hole are formed in sequence. , the third air outlet, the fourth air outlet and the fifth air outlet..., each row of air outlet holes are respectively connected to the first air outlet, the second air outlet, the third air outlet, the fourth air outlet and the fifth air outlet... on the side plate of the rotor shell through their respective connecting pipes, and each air outlet is respectively connected to the rear turbine through the corresponding first gas pipe, the second gas pipe, the third gas pipe, the fourth gas pipe and the fifth gas pipe..., an inner ring gas nozzle is provided in front of the turbine, and the first gas pipes of each first air outlet in the valve distribution angle area are respectively connected to the inner ring gas nozzle, and an inner ring nozzle static plate is provided at the jet port of the inner ring gas nozzle, and the inner ring gas nozzle is connected to the inner disk through the inner ring nozzle static plate, and the turbine The first-stage blades of 8 are located behind the inner-ring nozzle static piece in the inner-ring gas nozzle. The inner-ring gas nozzle is further extended backward, and the inner tube wall of the extended section is tapered outward to form an inner-ring expansion section. An inner-ring exhaust static piece is provided in the inner-ring expansion section. A second-stage gas nozzle is provided on the periphery of the inner-ring gas nozzle. The second gas pipes of the second gas outlet in each gas distribution angle zone are respectively connected to the second-stage gas nozzle. A second-stage nozzle static piece is provided at the jet port of the second-stage gas nozzle. The second-stage gas nozzle is connected to the periphery of the inner-ring gas nozzle via the second-stage nozzle static piece. The second-stage blades of the turbine are located behind the second-stage nozzle static piece in the second-stage gas nozzle. The second-stage gas nozzle is further extended backward, and the inner tube wall of the extended section is tapered. A secondary expansion section is formed outward, and a secondary exhaust static plate is provided in the secondary expansion section. A tertiary gas nozzle is provided on the periphery of the secondary gas nozzle. The third gas pipe of the third gas outlet in each gas distribution angle zone is respectively connected to the tertiary gas nozzle, and the tertiary blades of the turbine are placed in the tertiary gas nozzle. Similarly, a quaternary gas nozzle is provided on the periphery of the tertiary gas nozzle. The fourth gas pipe of the fourth gas outlet in each gas distribution angle zone is respectively connected to the quaternary gas nozzle, and the quaternary blades of the turbine are placed in the quaternary gas nozzle, until the corresponding gas pipes of each gas outlet in each gas distribution angle zone on the rotor shell are sequentially connected to the remaining corresponding gas nozzles that can blow the turbine blades.

[0005] When the number of gas nozzle stages is small but the number of gas pipes is large, the gas pipes of each outlet at the last stage can be connected to the annular pipe on the turbine housing, and the annular pipe is then connected to the corresponding vents on the turbine housing through several connecting pipes.

[0006] The connection between the gas pipe and the turbine casing can also be arranged in this way, so that the gas pipes at each gas outlet at the last stage are respectively connected to the gas surrounding pipes on the turbine casing at the corresponding position. The inner side of the gas surrounding pipe is then connected to the inner cavity air duct of the last stage guide stator fixed in the turbine casing through the air vent on the turbine casing. A long air jet slot is formed at the tail end of the last stage guide stator to blow the corresponding turbine blade.

[0007] When the rotor-supercharged gas turbine uses the output shaft to output power, a separate single-jet power turbine is provided outside the rotor-supercharged gas turbine on the output shaft in the casing, and the first gas pipes of each first air outlet in the valve distribution angle area on the side plate of the rotor casing are respectively led to the jet port of the single-jet power turbine, and the jet port is then aligned with the turbine blades of the single-jet power turbine. The air inlet corresponding to the jet port separated by the turbine blades is connected to the next jet port that blows the turbine blades through the return pipe. After the return pipe is set in multiple stages, the final exhaust end is connected to the exhaust pipe, and the second gas pipes of each second air outlet in the valve distribution angle area and the gas pipes of each subsequent air outlet are respectively led to the inner ring gas nozzle, the second-stage gas nozzle and the corresponding gas nozzles of each stage thereafter on the outside of the turbine.

[0008] In order to enable the single-jet power turbine to generate greater power, a second single-jet power turbine is also provided on the output shaft inside the casing. The first gas pipes of each first air outlet on the side plate of the rotor shell are divided into two. The divided branch gas pipes lead to the second jet port of the second single-jet power turbine. The air inlet corresponding to the second jet port is connected to the next jet port that blows the turbine blades through the return pipe. After the return pipe is set in multiple stages, the final exhaust end is connected to the exhaust pipe.

[0009] In addition, when the rotor supercharged gas turbine uses the output shaft to output power, the power turbine and the single-jet power turbine on the rear side of the gas turbine can also be set on the output shaft to output power together. In this arrangement, after the power turbine is provided on the rear side of the turbine in the turbine housing, an exhaust duct leading to the outside is formed behind the power turbine. The output shaft on the power turbine extends rearward through the exhaust duct. A single-jet power turbine installed in the housing is also provided on the rear side of the exhaust duct behind the power turbine. The single-jet power turbine is also fixed on the output shaft, and the first exhaust gas in the valve timing angle area on the rotor housing side plate is formed. The first gas pipes of the ports lead to the jet ports of the single-jet power turbine respectively, and the jet ports are then aimed at the turbine blades of the single-jet power turbine. The air inlets corresponding to the jet ports separated by the turbine blades are connected to the next jet ports aimed at the turbine blades through the return pipe. After the return pipe is arranged in multiple stages, the final exhaust end is connected to the exhaust duct through the exhaust pipe. The second gas pipes of each second outlet in the gas distribution angle area on the side plate of the rotor shell and the gas pipes of each subsequent outlet lead to the inner ring gas nozzle, the second-stage gas nozzle and the corresponding gas nozzles of each stage thereafter on the outside of the turbine respectively.

[0010] In a basic rotor-supercharged gas turbine, the pressure difference between the working gases in the different gas pipes ejected into the turbine can easily damage the turbine blades. In the multi-layered gas-injector-type rotor-supercharged gas turbine of the present invention, the working gases with the highest pressure are first directed from the first outlet through the inner ring gas nozzle to stably blow the first-stage turbine blades. After this working gas passes through the first-stage blades and its pressure is reduced, it joins the working gas with the correspondingly reduced pressure ejected from the second outlet to blow the second-stage turbine blades. This process continues in this manner, allowing the working gases ejected from the different gas pipes to blow the remaining turbine blades at a stable, gradually decreasing pressure. This prevents damage to the turbine blades, ensuring stable operation and high-efficiency power output. Furthermore, by providing a single-injection power turbine for the rotor-supercharged gas turbine, the working gases with the highest temperature and pressure are directed first to the turbine blades, while the working gases with relatively lower temperature and pressure are directed to the remaining turbine blades, thereby reducing the operating temperature of the turbine blades.

[0011] In practical applications, an intercooler that can significantly reduce the compressed air is set between the compressor and the rotor, allowing the rotor-supercharged gas turbine to achieve an isothermal compression Carnot cycle. This not only greatly improves the efficiency of the rotor-supercharged gas turbine, but also significantly reduces the operating temperature of the turbine blades because the cycle temperature will also be greatly reduced accordingly. As a result, the turbine blades do not need to be made of special high-temperature resistant materials, which is beneficial to reducing the production cost of the turbine.

[0012] BRIEF DESCRIPTION OF THE DRAWINGS The multi-layer gas nozzle type rotor supercharged gas turbine of the present invention will be described in detail below with reference to the accompanying drawings.

[0013] FIG1 is a cross-sectional view of the basic structure of a rotor-supercharged gas turbine.

[0014] FIG2 is a schematic diagram showing that each gas outlet on the rotor shell side plate disk in a rotor supercharged gas turbine is connected to the inner disk in front of the turbine through its own gas pipe.

[0015] FIG3 is a cross-sectional structural diagram of the multi-layer gas nozzle of the multi-layer gas nozzle type rotor supercharged gas turbine of the present invention.

[0016] FIG4 is a cross-sectional view of a second structure of the multi-layer gas nozzle of the multi-layer gas nozzle type rotor supercharged gas turbine of the present invention.

[0017] FIG5 is an enlarged cross-sectional view of the final guide vane in FIG4.

[0018] FIG6 is a cross-sectional structural diagram of a multi-layer gas nozzle type rotor supercharged gas turbine with a single-jet power turbine.

[0019] FIG7 is a cross-sectional structural diagram of a multi-layer gas nozzle type rotor supercharged gas turbine with a power turbine and a single-jet power turbine.

[0020] Specific implementation method The multi-layer gas nozzle type rotor supercharged gas turbine of the present invention is improved on the basis of the rotor supercharged gas turbine shown in Figure 1. In the basic rotor supercharged gas turbine, it includes a compressor 9, a rotor 29 and a turbine 8 connected by a machine shaft. The rotor is installed in a rotor shell 18, and a plurality of rows of combustion chambers 30 are provided on the rotor 29. The rotor shell 18 is divided into a number of equal valve timing angle zones 40 (see Figure 2). From the starting position in each valve timing angle zone 40 on the rotor shell 18 to the end position along the rotation direction of the rotor 29 (as shown by the arrow 36), there are ventilation inlet holes 27 and ventilation outlet holes 28 at the same angle in sequence. The outlet end of the compressor 9 is connected to the ventilation inlet hole 27 on the rotor shell 18 through the compressed air pipe 20. The compressed air pipe 20 is provided with an injector 80. The compressed air from the compressor 9 is first formed into a homogeneous fuel-fuel mixture in the compressed air pipe. After the ventilation inlet hole 27 on the rotor shell 18 communicates with the combustion chamber 30 on the rotor 29, it is filled into the combustion chamber and squeezes the medium-pressure working gas in the combustion chamber out of the combustion chamber. The medium-pressure working gas is then discharged from the ventilation outlet hole 28 through the corresponding air supply pipe 17 to the turbine 8 on the rear side. After the ventilation inlet and outlet holes, an ignition chamber equipped with a spark plug, a first outlet hole, a second outlet hole, a third outlet hole, a fourth outlet hole and a fifth outlet hole... are formed in sequence. The outlet holes in each row are then connected to the first outlet 1, the second outlet 2, the third outlet 3, the fourth outlet 4 and the fifth outlet 5... on the rotor shell side plate 19 through their respective connecting pipes. The arrangement of the outlets on the rotor shell side plate 19 is shown in Figure 2. The outlets are then connected to the turbine 8 on the rear side through the corresponding first gas pipe 11, the second gas pipe 12, the third gas pipe 13, the fourth gas pipe 14 and the fifth gas pipe 15... As shown in Figure 2, six outlet holes are sequentially arranged within a valve timing angle zone on the rotor housing 18. Accordingly, a first outlet 1, a second outlet 2, a third outlet 3, a fourth outlet 4, a fifth outlet 5, and a sixth outlet 6 are also formed within a valve timing angle zone 40 on the rotor housing side plate 19. These six outlets are then connected to corresponding valve timing angle zones 40' on the inner disc 37 at the front of the turbine 8 via respective first gas pipes 11, second gas pipes 12, third gas pipes 13, fourth gas pipes 14, fifth gas pipes 15, and sixth gas pipes 16. The seventh outlet 7 is a ventilation outlet. During medium-pressure ventilation, the medium-pressure working gas discharged from the combustion chamber 30 is discharged to the rear turbine via the gas transmission pipe 17.Since the working gas ejected from the first gas pipe 11 has the highest pressure, the working gas pressure ejected from the remaining gas pipes gradually decreases, resulting in a certain pressure difference between the working gases in adjacent gas pipes, which in turn subjects the turbine blades to certain pulsating shocks. Although the gas pipe ends on the inner disk 37 are rationally arranged, with the outlet end 1' of the first gas pipe 11, which has the highest working gas pressure, located in the middle, and the outlet ends 7', 5', 3', 1', 2', 4', and 6' of the various gas pipes arranged to the sides in descending order of pressure, the pulsating pressure of the working gas ejected from adjacent gas pipes is not very large, allowing the turbine blades to withstand it. However, this pulsating pressure of the working gas does damage the blade structure and is not conducive to the stable operation of the turbine blades. In addition, the working gases of different pressures, after flowing through the turbine blades, form a turbulent airflow, which is not conducive to the power conversion of the working gas.

[0021] To overcome these shortcomings of the basic rotor-supercharged gas turbine, the present invention provides a multi-layer gas nozzle-type rotor-supercharged gas turbine. This improved rotor-supercharged gas turbine, as shown in Figures 3 and 4, builds upon the basic rotor-supercharged gas turbine by connecting each gas pipe extending from the rotor shell side plate 19 to a corresponding plurality of nested gas nozzles. The working gas of varying pressures ejected from each gas nozzle then blows the blades of the turbine at different stages. In the multi-layer gas nozzle-type rotor-supercharged gas turbine shown in Figure 3, while only four gas pipes are provided on the rotor shell side plate 19, four gas nozzles can be provided for the turbine 8: an inner ring gas nozzle 21, a second-stage gas nozzle 31, a third-stage gas nozzle 41, and an outermost fourth-stage gas nozzle 51. Correspondingly, a first gas pipe 11 leading to the inner ring gas injector 21, a second gas pipe 12 leading to the second-stage gas injector 31, a third gas pipe 13 leading to the third-stage gas injector 41, and a fourth gas pipe 14 leading to the fourth-stage gas injector 51 are connected from the rotor shell side plate 19, thereby forming a multi-layer gas injector type rotor supercharged gas turbine. The structure of each gas nozzle is shown in Figure 3. After the inner ring gas nozzle 21 is arranged in front of the turbine 8, the first gas pipe 11 of each first gas outlet in the valve angle zone 40 is respectively connected to the inner ring gas nozzle 21. An inner ring nozzle static vane 22 is provided at the nozzle of the inner ring gas nozzle. The inner ring gas nozzle is connected to the inner disk 37 via the inner ring nozzle static vane 22. The first-stage blade 61 of the turbine 8 is located on the rear side of the inner ring nozzle static vane 22 in the inner ring gas nozzle 21. The inner ring gas nozzle 21 is further extended backward, and the inner cylinder wall of the extended section is tapered outward to form an inner ring expansion section 23. An inner ring exhaust static vane 24 is provided in the inner ring expansion section.

[0022] The working gas ejected from the first gas pipe 11 has the highest pressure because it has just completed the constant volume combustion process in the combustion chamber 30 on the rotor. Therefore, this part of the working gas with the highest pressure enters the inner ring gas nozzle 21 first, is guided by the inner ring nozzle static plate 22 on the rear side of the inner ring gas nozzle, and then is ejected to the first-stage blade 61 on the turbine 8. The working gas flowing through the first-stage blade passes through the inner ring expansion section 23 and the inner ring exhaust static plate 24 on the rear side thereof, and its pressure is reduced accordingly before being discharged backwards.

[0023] A secondary gas nozzle 31 is provided on the periphery of the inner ring gas nozzle 21. The second gas pipe 12 of the second gas outlet in each gas distribution angle zone 40 is respectively connected to the secondary gas nozzle 31. A secondary nozzle static piece 32 is provided at the nozzle of the secondary gas nozzle. The secondary gas nozzle is connected to the periphery of the inner ring gas nozzle 21 via the secondary nozzle static piece 32. The secondary blades 62 of the turbine 8 are located on the rear side of the secondary nozzle static piece 32 in the secondary gas nozzle 31. The secondary gas nozzle 31 is further extended rearward, and the inner cylinder wall of the extended section is tapered outward to form a secondary expansion section 33. A secondary exhaust static piece 34 is provided in the secondary expansion section.

[0024] The pressure of the working gas ejected from the second gas pipe 12 is correspondingly lower than the pressure of the working gas ejected from the first gas pipe 11. This part of the working gas with a correspondingly reduced pressure is guided by the secondary gas nozzle 31 and the secondary nozzle static plate 32, and is sprayed onto the large diameter blade of the secondary blade 62 on the turbine 8. The working gas discharged from the inner ring exhaust static plate 24 on the rear side of the inner ring gas nozzle 21 is sprayed onto the blade close to the root of the secondary blade 62.

[0025] A tertiary gas nozzle 41 is provided on the periphery of the secondary gas nozzle 31. The third gas pipe 13 of the third gas outlet in each gas distribution angle zone 40 is respectively connected to the tertiary gas nozzle 41, and the tertiary blade 63 of the turbine 8 is located in the tertiary gas nozzle 41. Similarly, a quaternary gas nozzle 51 is provided on the periphery of the tertiary gas nozzle 41. The fourth gas pipe 14 of the fourth gas outlet in each gas distribution angle zone 40 is respectively connected to the quaternary gas nozzle 51, and the quaternary blade 64 of the turbine 8 is located in the quaternary gas nozzle 51, until the corresponding gas pipes of each gas outlet in each gas distribution angle zone 40 on the rotor shell 18 are sequentially connected to the remaining corresponding gas nozzles that can blow the turbine blades.

[0026] The pressure of the working gas ejected from the third gas pipe 13 will also decrease accordingly. This part of the working gas is guided by the third-stage gas nozzle 41 and the third-stage nozzle stator 42, and then sprayed onto the blades with large diameter of the third-stage blade 63 on the turbine 8, while the blades in the middle and root of the third-stage blade 63 are blown by the working gas discharged from the second-stage blade 62 and the second-stage exhaust stator 34.

[0027] The pressure of the working gas ejected from the fourth gas pipe 14 will be further reduced. This part of the working gas is guided by the fourth-stage gas nozzle 51 and the fourth-stage nozzle stator 52, and then sprayed onto the blades at the large-diameter outer ends of the fourth-stage blades 64 on the turbine 8, while most of the blades inside the fourth-stage blades 64 are blown by the working gas discharged from the third-stage blades 63 and the third-stage exhaust stator 44 on the turbine 8. The working gas discharged from the third-stage exhaust stator 44 already includes the working gas from the first gas pipe 11, the second gas pipe 12 and the third gas pipe 13.

[0028] Since the structure of the multi-layer gas nozzle is relatively complex, when the number of gas pipes connected from the rotor shell side plate 19 is large, for the multi-layer gas nozzle type rotor supercharged gas turbine shown in Figure 4, when six outlet holes are provided on the rotor shell for the working gas, six gas pipes are correspondingly connected to the rotor shell side plate 19. If a four-stage gas nozzle is still provided for this rotor supercharged gas turbine, the gas pipes 15 and gas pipes 16 of each outlet at the final stage position can also be arranged as follows. As shown in Figure 4, the gas pipe 15 connected from the rotor shell side plate 19 leads to the annular pipe 55 on the turbine shell 38. This annular pipe is then connected to the corresponding vents 57 on the turbine shell 38 through a number of joint pipes 56, allowing the low-pressure working gas to enter the turbine shell from the vents on the turbine shell 38 to blow the blades 65 on the rear side of the turbine 8. The gas pipe 16 can also be arranged like the gas pipe 15. A corresponding ring pipe and a joint pipe 56 connected to the turbine housing are arranged on the rear side of the upper ring pipe 55 of the turbine housing 38, so that each gas pipe 16 is connected to the ring pipe on the rear side.

[0029] Furthermore, the gas pipes 16 at the final stage outlets can be arranged so that each gas pipe 16 is connected to a corresponding gas conduit 68 on the turbine housing 38. The inner side of the gas conduit then communicates with the inner cavity air passage 59 of the final stage guide vane 58 fixed within the turbine housing through an air vent 69 on the turbine housing. A jet slit 60 is formed at the rear end of the final stage guide vane 58 to blow the corresponding turbine blades. This allows low-pressure working gas to flow from the gas conduit 68 on the turbine housing 38 along the inner cavity air passage 59 of the final stage guide vane 58 and out of the jet slit 60 of the final stage guide vane to blow the rear blades 66 of the turbine 8. The cross-sectional shape of the final stage guide vane 58 is shown in the enlarged cross-sectional view of FIG5. To strengthen the jet slit 60 of the final stage guide vane, connecting ribs 78 are formed at both sides of the jet slit.

[0030] In a multi-layer gas nozzle type rotor supercharged gas turbine, since the first-stage blades 61 of the turbine 8 will be blown by the working gas with the highest temperature and maximum pressure, in order to significantly improve the efficiency of the rotor supercharged gas turbine, in practice, an intercooler that can significantly reduce the temperature is set between the compressor and the rotor. After the rotor supercharged gas turbine realizes the isothermal compression Carnot cycle, the compressed air is easier to be compressed after being cooled, which greatly reduces the compression consumed by the compressor and greatly reduces the maximum combustion temperature and exhaust temperature. This not only greatly improves the efficiency of the rotor supercharged gas turbine, but also significantly reduces the operating temperature of the first-stage blades 61 and other rear blades of the turbine 8, thereby greatly improving the working conditions of the turbine blades.

[0031] In order to facilitate the use of the shaft output power of the gas turbine, a separate single-jet power turbine can also be provided for the multi-layer gas-injection rotor supercharged gas turbine. As shown in FIG6 , when the gas turbine is allowed to output power outward through the output shaft, a separate single-jet power turbine 48 is provided on the output shaft 46 in the shell 45 in addition to the multi-layer gas-injection rotor supercharged gas turbine. The first gas pipes 11 of each first gas outlet in the valve distribution angle area 40 on the side plate of the rotor shell are respectively led to the jet ports 47 of the single-jet power turbine 48, and the jet ports are then aligned with the turbine blades 49 of the single-jet power turbine. The air inlet 25 corresponding to the jet ports 47 separated by the turbine blades 49 is connected to the next jet port that blows the turbine blades 49 through the return line 26, so that the working gas flowing from the turbine blades 49 can return to the next jet port aligned with the turbine blades 49 along the return line 26 to continue blowing the turbine blades to rotate and work. The multi-stage return line 26 is equivalent to providing a single-jet power turbine 48 with multiple stages of turbine blades. This allows the high-pressure working gas flowing through the turbine blades to repeatedly blow against the turbine blades 49 through the return line 26. The final exhaust end is then connected to the exhaust pipe 50, allowing the working gas to fully expand and perform work multiple times before being discharged from the exhaust pipe 50. After the first gas pipe 11 is connected to the air jet 47 of the single-jet power turbine 48 to blow against the turbine blades 49, the second gas pipe 12 of each second outlet within the gas distribution angle area 40 and the subsequent gas pipes of each outlet are respectively connected to the inner ring gas injector 21, the secondary gas injector 31, and the corresponding gas injectors at each subsequent stage outside the turbine 8.

[0032] If the power output of a single-jet power turbine is low, a second single-jet power turbine 70 can be installed on the output shaft 46 within the housing 45. The first gas pipe 11 of each first gas outlet on the rotor shell side plate is split into two, with the branched gas pipe 71 leading to the second gas outlet 72 of the second single-jet power turbine 70. The gas inlet 73 corresponding to the second gas outlet is then connected to the next gas outlet that blows the turbine blades 49 via a return line 74. The return line 74 is arranged in multiple stages, with the final exhaust end connected to the exhaust pipe 50. By installing the single-jet power turbine 48 and the second single-jet power turbine 70 on the output shaft 46, the two power turbines are subjected to symmetrical working gas forces, thereby eliminating the axial thrust on the output shaft 46 and facilitating the reduction of the axial load on the output shaft bearings.

[0033] In a multi-layer gas-injection rotor supercharged gas turbine, when the gas turbine uses the output shaft to output power outward, if a power turbine 35 is set on the rear side of the turbine 8 in the turbine housing 38, in order to be able to set a single-injection power turbine behind the power turbine, an exhaust duct 76 leading to the outside is formed behind the power turbine 35, and the output shaft 46 on the power turbine 35 extends backward through the exhaust duct 76. In order to obtain greater shaft output power, a single-jet power turbine 48 is provided on the rear side of the exhaust duct 76 behind the power turbine 35 and is installed in the shell 45. As shown in Figure 7, the single-jet power turbine is also fixed on the output shaft 46, and the first gas pipes 11 of each first gas outlet in the valve angle area 40 on the side plate of the rotor shell are respectively connected to the jet ports 47 of the single-jet power turbine 48, and the jet ports are then aligned with the turbine blades 49 of the single-jet power turbine. The air inlet 25 corresponding to the jet port 47 separated by the turbine blades 49 is connected to the next jet port aligned with the turbine blades 49 through the return line 26, so that the working gas flowing from the turbine blades 49 can be blown along the return line 26 to blow the turbine blades to rotate and work again. After the return line 26 is arranged in multiple stages, the final exhaust end is connected to the exhaust duct 76 through the exhaust pipe 75, and the second gas pipe 12 of each second outlet in the valve angle area 40 on the side plate of the rotor shell and the gas pipes of each subsequent outlet are respectively led to the inner ring gas nozzle 21, the secondary gas nozzle 31 and the corresponding gas nozzles of each level thereafter on the outside of the turbine 8.

[0034] In the multi-layer gas-injection type rotor-supercharged gas turbine shown in FIG6 , if an intercooler is used to allow the rotor-supercharged gas turbine to perform a Carnot cycle, the working gas at the highest temperature and maximum pressure discharged from the first gas pipe 11 first enters the power casing 45 to blow the power turbine 48 on the output shaft 46. The working gas, whose temperature and pressure have been further reduced, then passes through the second gas pipe 12 and the inner ring gas injector 21 to blow the first-stage blades 61 of the turbine 8. This is more conducive to improving the operating conditions of the first-stage blades and other rear-stage blades on the turbine.

Claims

1. Multi-layer gas spray type rotor supercharged gas turbine, comprising a compressor (9), a rotor (29) and a turbine (8) connected by a machine shaft, the rotor is installed in a rotor housing (18), several rows of combustion chambers (30) are provided on the rotor (29), several equal distribution angle areas (40) are divided on the rotor housing (18), from the starting position within each distribution angle area (40) on the rotor housing (18) to the end position in the rotating direction of the rotor (29), an air exchange inlet hole (27) and an air exchange outlet hole (28) at the same angle are successively provided, the air outlet end of the compressor (9) is connected to the air exchange inlet hole (27) on the rotor housing (18) through a compressed air pipe (20), the air exchange outlet hole (28) is connected to the turbine (8) at the rear through a corresponding gas transmission pipe (17), after the air exchange inlet hole and the air exchange outlet hole, an ignition chamber equipped with a spark plug, a first air outlet hole, a second air outlet hole, a third air outlet hole, a fourth air outlet hole and a fifth air outlet hole... are successively formed, the air outlet holes of each row are respectively connected to 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 (5)... on the side plate disc (19) of the rotor housing through respective connecting pipes, each air outlet is respectively connected to the turbine (8) at the rear through a corresponding first gas pipe (11), a second gas pipe (12), a third gas pipe (13), a fourth gas pipe (14) and a fifth gas pipe (15)..., and it is characterized in that: Before the turbine (8), there is an inner ring gas nozzle (21). The first gas pipes (11) of the first air outlets in each gas distribution angle area (40) are respectively connected to the inner ring gas nozzle (21). At the jet outlet of the inner ring gas nozzle, there is an inner ring nozzle stationary vane (22). The inner ring gas nozzle is connected to the inner side disc (37) through the inner ring nozzle stationary vane (22). The first-stage blades (61) of the turbine (8) are located at the rear of the inner ring nozzle stationary vane (22) inside the inner ring gas nozzle (21). The inner ring gas nozzle (21) extends backward, and the inner barrel wall of its extension section forms a conical shape outward to form an inner ring expansion section (23). Inside the inner ring expansion section, there is an inner ring exhaust stationary vane (24). Around the inner ring gas nozzle (21), there is a second-stage gas nozzle (31). The second gas pipes (12) of the second air outlets in each gas distribution angle area (40) are respectively connected to the second-stage gas nozzle (31). At the jet outlet of the second-stage gas nozzle, there is a second-stage nozzle stationary vane (32). The second-stage gas nozzle is connected to the periphery of the inner ring gas nozzle (21) through the second-stage nozzle stationary vane (32). The second-stage blades (62) of the turbine (8) are located at the rear of the second-stage nozzle stationary vane (32) inside the second-stage gas nozzle (31). The second-stage gas nozzle (31) extends backward, and the inner barrel wall of its extension section forms a conical shape outward to form a second-stage expansion section (33). Inside the second-stage expansion section, there is a second-stage exhaust stationary vane (34). Around the second-stage gas nozzle (31), there is a third-stage gas nozzle (41). The third gas pipes (13) of the third air outlets in each gas distribution angle area (40) are respectively connected to the third-stage gas nozzle (41), and the third-stage blades (63) of the turbine (8) are located inside the third-stage gas nozzle (41). And so on. Around the third-stage gas nozzle (41), there is a fourth-stage gas nozzle (51). The fourth gas pipes (14) of the fourth air outlets in each gas distribution angle area (40) are respectively connected to the fourth-stage gas nozzle (51), and the fourth-stage blades (64) of the turbine (8) are located inside the fourth-stage gas nozzle (51), until the corresponding gas pipes of the air outlets in each gas distribution angle area (40) on the rotor housing (18) are successively connected to the remaining corresponding gas nozzles that can blow the turbine blades.

2. The multi-layer gas nozzle type rotor supercharged gas turbine according to claim 1, characterized in that: The gas pipes (15) of the air outlets in the last stage position lead to the annular pipe (55) on the turbine housing (38), and the annular pipe is respectively connected to the ventilation ports (57) on the corresponding turbine housing (38) through several connecting pipes (56).

3. The multi-layer gas nozzle type rotor supercharged gas turbine according to claim 1, characterized in that: The gas pipes (16) of the air outlets in the last stage position are respectively connected to the gas surrounding pipes (68) on the corresponding turbine housing (38). The inner side of the gas surrounding pipe (68) is then connected to the inner cavity ventilation channel (59) of the last-stage guide stationary vane (58) fixed inside the turbine housing through the ventilation port (69) on the turbine housing. At the tail end of the last-stage guide stationary vane (58), there is a jet long slit (60) that blows the corresponding turbine blades.

4. The multi-layer gas nozzle type rotor supercharged gas turbine according to claim 1, 2 or 3, characterized in that: Outside the turbocharged gas turbine, there is a single-jet power turbine (48) separately installed on the output shaft (46) within the housing (45). The first gas pipes (11) of the first gas outlets in the gas distribution angle area (40) on the rotor housing side plate disc respectively lead to the jet ports (47) of the single-jet power turbine (48). The jet ports are then aligned with the turbine blades (49) of the single-jet power turbine. The gas intake ports (25) corresponding to the jet ports (47) separated by the turbine blades (49) are then connected through the return pipeline (26) to the next jet port that blows the turbine blades (49). After the return pipeline (26) is set up in multiple stages, the final exhaust end is then connected to the exhaust pipe 50. The second gas pipes (12) of the second gas outlets in the gas distribution angle area (40) and the gas pipes of the subsequent gas outlets respectively lead to the inner ring gas nozzles (21), the second-stage gas nozzles (31), and the corresponding subsequent-stage gas nozzles outside the turbine (8).

5. The multi-layer gas spray type rotor supercharged gas turbine according to claim 4, characterized in that: On the output shaft (46) within the housing (45), there is a second single-jet power turbine (70). The first gas pipes (11) of the first gas outlets on the rotor housing side plate disc are divided into two. The branched gas pipes (71) separated lead to the second jet ports (72) of the second single-jet power turbine (70). The gas intake ports (73) corresponding to the second jet ports are then connected through the return pipeline (74) to the next jet port that blows the turbine blades (49). After the return pipeline is set up in multiple stages, the final exhaust end is then connected to the exhaust pipe 50.

6. The multi-layer gas spray type rotor supercharged gas turbine according to claim 4, characterized in that: After a power turbine (35) is provided at the rear of the turbine (8) within the turbine housing (38), an exhaust passage (76) leading to the outside is formed behind the power turbine (35). The output shaft (46) on the power turbine (35) passes through the exhaust passage (76) and extends backward. At the rear side of the exhaust passage (76) behind the power turbine (35), there is also a single-jet power turbine (48) installed within the housing (45). This single-jet power turbine is also fixed on the output shaft (46). The first gas pipes (11) of the first gas outlets in the gas distribution angle area (40) on the rotor housing side plate disc respectively lead to the jet ports (47) of the single-jet power turbine (48). The jet ports are then aligned with the turbine blades (49) of the single-jet power turbine. The gas intake ports (25) corresponding to the jet ports (47) separated by the turbine blades (49) are then connected through the return pipeline (26) to the next jet port aligned with the turbine blades (49). After the return pipeline (26) is set up in multiple stages, the final exhaust end is then connected to the exhaust passage (76) through the exhaust pipe (75). The second gas pipes (12) of the second gas outlets in the gas distribution angle area (40) on the rotor housing side plate disc and the gas pipes of the subsequent gas outlets respectively lead to the inner ring gas nozzles (21), the second-stage gas nozzles (31), and the corresponding subsequent-stage gas nozzles outside the turbine (8).

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