CN111963313A - Rotor supercharging gas turbine - Google Patents
Rotor supercharging gas turbine Download PDFInfo
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- CN111963313A CN111963313A CN202010847769.2A CN202010847769A CN111963313A CN 111963313 A CN111963313 A CN 111963313A CN 202010847769 A CN202010847769 A CN 202010847769A CN 111963313 A CN111963313 A CN 111963313A
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- rotor
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- 238000002485 combustion reaction Methods 0.000 claims abstract description 141
- 238000009423 ventilation Methods 0.000 claims description 42
- 238000002347 injection Methods 0.000 claims description 14
- 239000007924 injection Substances 0.000 claims description 14
- 238000006073 displacement reaction Methods 0.000 claims description 5
- 239000000446 fuel Substances 0.000 claims description 4
- 230000000149 penetrating effect Effects 0.000 claims description 2
- 239000007789 gas Substances 0.000 description 71
- 238000010926 purge Methods 0.000 description 6
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 239000002912 waste gas Substances 0.000 description 1
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/30—Exhaust heads, chambers, or the like
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/045—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for noise suppression
Abstract
In the rotor supercharged gas turbine of application No. 202010650212.X, although the efficiency is improved by increasing the gas pressure of working gas entering the turbine between the compressor and the turbine by adding the rotor, the quantity of air flowing through the gas turbine is limited by the rotor, so that the output power is obviously reduced, in the rotor supercharged gas turbine of the invention, besides the first row of combustion chambers (45) arranged on the rotor (41), the second row and the third row of combustion chambers are added after the first row of combustion chambers, correspondingly, the rotor shell (28) is also provided with corresponding air pipes communicated with the rows of combustion chambers and communicated with the turbine (25), after adopting the structure of the rows of combustion chambers, the air exchange of each combustion chamber can be rapidly completed, and simultaneously, the added combustion chambers basically contain the quantity of air entering the gas turbine, so that the efficiency is improved, the gas turbine can output large power.
Description
The invention relates to a gas turbine, in particular to a rotor supercharging gas turbine.
In the rotor supercharged gas turbine with application number of 202010650212.X, although the gas pressure of the gas entering the turbine to do work is increased by adding a rotor structure between the gas compressor and the turbine, the efficiency of the gas turbine is further increased, the amount of air flowing through the gas turbine is greatly limited by the arranged rotor, and the output power of the rotor supercharged gas turbine is obviously reduced compared with that of a common gas turbine.
Summary of the inventionit is an object of the present invention to provide an improved gas turbine with a supercharged rotor which, while having a high efficiency, does not reduce the output power much compared to conventional gas turbines.
The rotor supercharged gas turbine of the invention comprises a gas compressor and a turbine connected through a crankshaft, wherein a rotor is arranged between the gas compressor and the turbine, the rotor is arranged in a rotor shell, a plurality of pit type combustion chambers with the same shape and the same interval distance are densely arranged on the rotor in the circumferential direction, two or more than two equal gas distribution angle areas are divided on the rotor shell, a gas exchange inlet and a gas exchange outlet which are positioned in the same angle, a fuel injection cavity provided with a fuel injector, an ignition cavity provided with a spark plug and a plurality of first air outlet, second air outlet, third air outlet, fourth air outlet and fifth air outlet … … which are sequentially arranged from the initial position of each gas distribution angle area on the rotor shell to the tail end position along the rotation direction of the rotor and correspond to the positions of the combustion chambers on the rotor, wherein, a compressed air outlet of the gas compressor is communicated with the gas exchange inlet on the rotor shell, the air exchange outlet on the rear side of the rotor shell is communicated with the turbine, when the rotor rotates along with the turbine, the combustion chamber on the rotor which is sequentially turned over can simultaneously communicate the air exchange inlet and the air exchange outlet on the rotor shell when the rotor is turned to the positions of the air exchange inlet and the air exchange outlet, the front side of the turbine is provided with a nozzle disc, the nozzle disc is also divided into a plurality of air distribution angle areas which are the same as and correspond to the plurality of air distribution angle areas on the rotor shell, the air exchange outlet, a first air outlet, a second air outlet, a third air outlet, a fourth air outlet and a fifth air outlet … … which are arranged on each plurality of air distribution angle areas on the rotor shell are respectively arranged along respective air conveying pipes in a displacement way and then sequentially communicated with the air exchange nozzle, a … … fifth air nozzle, a third air nozzle, a first air nozzle, a second air nozzle and a fourth air nozzle … … in the following order in each air distribution angle area on the nozzle disc, the first air outlet on the rotor shell is arranged in the order from the maximum pressure to the gradually reduced pressure, and is connected to the nozzle plate through the displacement arrangement at the other end of the air pipe, then becomes the maximum pressure air outlet with the first air nozzle communicated with the first air outlet as the middle position, then the pressing force of the other air nozzles is arranged in the order of decreasing pressure to the left and right sides of the first air nozzle, besides the first row of combustion chambers are arranged on the circumferential surface of the rotor, the second row of combustion chambers and the third row of combustion chambers … … are additionally arranged in the turbine side direction at a certain distance behind the first row of combustion chambers, correspondingly, the rotor shell is also provided with a ventilation inlet, a second ventilation inlet and a third ventilation inlet … … close to the compressor side and a ventilation outlet close to the turbine side, which can be communicated with the first row of combustion chambers, the second row of combustion chambers and the third row of combustion chambers … …, The second ventilation outlet … … is connected with the air delivery pipes from the compressed air outlet of the compressor through the first inflation manifold, the second inflation manifold and the third inflation manifold … …, respectively, and is connected with the corresponding ventilation inlet, the second ventilation inlet … … on the rotor shell, the ventilation outlet, the second ventilation outlet and the third ventilation outlet … … on the rotor shell are connected with the corresponding ventilation air delivery pipes through the respective first air outlet manifold, the second air outlet manifold and the third air outlet manifold … …, and the air delivery pipes are connected with the ventilation nozzles in the corresponding air distribution angle area on the nozzle plate; corresponding to the first row of combustion chambers, the second row of combustion chambers and the third row of combustion chambers … … on the rotor, oil injection cavities provided with oil injectors, a second oil injection cavity and a third oil injection cavity … … are correspondingly arranged on the rotor shell, and then ignition cavities provided with spark plugs, a second ignition cavity and a third ignition cavity … … are correspondingly arranged; in order to make the first row of combustion chambers, the second row of combustion chambers and the third row of combustion chambers … … on the rotor communicate with the first air outlet, the second air outlet, the third air outlet, the fourth air outlet and the fifth air outlet … … arranged behind the ignition cavity on the rotor shell in sequence, each air outlet on the rotor shell is made into a corresponding number of small air outlets to communicate with a plurality of rows of combustion chambers on the rotor, or each air outlet on the rotor shell is made into a long air outlet to communicate with a plurality of rows of combustion chambers on the rotor, then each group of air outlets are arranged in a deflection way through respective air delivery pipes and then communicate with corresponding air nozzles on the nozzle plate leading to the turbine.
In order to enable each air outlet on the rotor shell to be communicated with a first row of combustion chambers, a second row of combustion chambers and a third row of combustion chambers on the rotor, after each air outlet of each air outlet on the rotor shell is made into a corresponding number of small air outlets to be communicated with a plurality of rows of combustion chambers on the rotor simultaneously, each small air outlet is communicated with a corresponding air delivery pipe through a respective air outlet manifold, an air outlet two manifold and an air outlet three manifold, and the other end of each corresponding air delivery pipe is communicated with a corresponding air jet port on the nozzle plate after being arranged in a deflection mode.
In order to reduce the pressure fluctuation when a plurality of rows of combustion chambers on the rotor are communicated with each air outlet, in each group of small air outlets sequentially communicated with corresponding air conveying pipes on the rotor shell, the small air outlet connected with the air outlet manifold is taken as a reference, each small air outlet at the later position is staggered by a certain angle relative to the small air outlet at the front along the rotation direction (or the reverse direction) of the rotor, and the total staggered angle of the small air outlets is smaller than the angle occupied by one combustion chamber on the rotor.
If each group of small air outlets of the air outlets on the rotor shell are still aligned with the central axis, in the first row of combustion chambers, the second row of combustion chambers and the third row of combustion chambers … … on the rotor, each row of combustion chambers can be inclined or staggered at a certain angle relative to the combustion chambers on the front row along the rotation direction (or reverse direction) of the rotor, but the total inclined or staggered angle of the inclined or staggered combustion chambers is smaller than the angle occupied by one small air outlet on the rotor shell.
In order to communicate each air outlet on the rotor shell with the first row of combustion chambers, the second row of combustion chambers and the third row of combustion chambers on the rotor, a long air outlet which can communicate a plurality of rows of combustion chambers on the rotor is formed by a long concave air outlet cavity arranged on the inner wall of the rotor shell, each air outlet cavity is communicated with a corresponding first air delivery pipe, a second air delivery pipe, a third air delivery pipe, a fourth air delivery pipe and a fifth air delivery pipe … … through a corresponding air outlet close to the turbine side, and the other end of each air delivery pipe is communicated with a corresponding air jet on the nozzle disk after being arranged in a displacement manner.
In order to reduce pressure fluctuation when a plurality of rows of combustion chambers on the rotor are communicated with each long air outlet, each long air outlet on the rotor shell is inclined at a certain angle along the rotation direction (or the reverse direction) of the rotor, but the total inclined angle occupies a width smaller than the opening angle width of the combustion chambers on the rotor.
If the elongated outlets in the rotor housing are aligned with the central axis, the first row of combustion chambers, the second row of combustion chambers, and the third row of combustion chambers … … in the rotor can be tilted or staggered at an angle relative to the combustion chambers in the front row in the direction (or reverse direction) of the rotation of the rotor, but the total angle of the tilt or stagger of the combustion chambers is smaller than the opening angle of one elongated outlet in the rotor housing.
In order to adjust the gap distance between the rotor and the rotor shell, the rotor is made into a truncated cone-shaped sliding sleeve structure and is arranged on a shaft drum penetrating through a machine shaft of the rotor, so that the rotor can be fixed after being well adjusted to the small-diameter side of the rotor shell.
And a connecting vent pipe is arranged on the connecting shell between the rotor and the turbine, the other end of the connecting vent pipe is communicated with a vent hole on the turbine shell at the corresponding position behind the first-stage turbine or the second-stage turbine, and the vent hole is positioned at the position with the minimum airflow pressure in the turbine shell. In addition, a connecting breather pipe is also arranged on a connecting shell between the rotor and the compressor, and the other end of the connecting breather pipe is communicated with a vent hole on the compressor shell at a position with slightly lower pressure.
In the original rotor supercharged gas turbine, because the rotor is provided with only one row of combustion chambers, when the size of the combustion chambers is prolonged for increasing the air capacity, the compressed air in the combustion chambers and the waste gas after doing work can not be well exchanged quickly. In the rotor supercharged gas turbine of the invention, because the second row of combustion chambers and the third row of combustion chambers … … are additionally arranged at certain intervals after the first row of combustion chambers of the rotor, each combustion chamber can be quickly ventilated, and simultaneously, a plurality of rows of combustion chambers can be arranged according to the requirement of air inflow to increase the ventilation volume, thereby still achieving great output power of the rotor supercharged gas turbine. After more rows of combustion chambers are arranged on the rotor, the axial leakage of working gas in the middle combustion chamber is reduced. In addition, after each group of small air outlets on the rotor shell are arranged in a staggered way at a certain angle along the rotation direction of the rotor, the staggered small air outlets can be sequentially communicated with a plurality of rows of combustion chambers on the rotor, so that the pressure fluctuation of working gas when the combustion chambers are communicated with the air outlets is correspondingly reduced, and the reduction of the operation noise of the gas turbine is facilitated.
Description of the drawings the following provides a detailed description of a rotor supercharged gas turbine according to the invention with reference to the drawings.
FIG. 1 is a general block diagram of a rotor supercharged gas turbine of the present invention.
FIG. 2 is a cross-sectional view of the rotor supercharged gas turbine along line A-A of FIG. 1.
FIG. 3 is a cross-sectional view of the fuel injector arrangement and rotor combustion chamber taken along line B-B of FIG. 2.
FIG. 4 is a cross-sectional view of the spark plug arrangement and rotor combustion chamber taken along line C-C of FIG. 2.
FIG. 5 is a sectional view of the connection of each of the small air outlets and the first air delivery conduit, taken along line D-D in FIG. 2.
FIG. 6 is a view showing the arrangement of the small air outlets on the rotor case staggered at a certain angle.
FIG. 7 is an angled arrangement of combustion chambers on a rotor.
FIG. 8 is a sectional view showing the connection between the elongated air outlet and the first air delivery pipe of the rotor case.
Fig. 9 is a view of the angular disposition of the elongated air outlets in the rotor shell.
FIG. 10 is an angled arrangement of combustion chambers on a rotor.
Detailed description of the inventionas shown in fig. 1 and 2, compared with the conventional rotor supercharged gas turbine, the rotor supercharged gas turbine of the present invention also includes a compressor 9 and a turbine 25 connected by a crankshaft 23, a rotor 41 is provided between the compressor 9 and the turbine 25, the rotor is mounted in a rotor case 28, and a plurality of pit type combustion chambers 45 having the same shape and the same interval distance are densely arranged on the rotor 41 in the circumferential direction. The rotor housing 28 is divided into two or more equal distribution angle areas 40, and in fig. 2, the rotor housing 28 is divided into four distribution angle areas 40. From the initial position of each air distribution angular zone 40 on the rotor shell 28 to the terminal position along the rotation direction of the rotor 41 and corresponding to the position of the combustion chamber 45 on the rotor, a ventilation inlet 31 and a ventilation outlet 7 which are positioned in the same angle, an oil injection cavity 34 provided with an oil injector 35, an ignition cavity 36 provided with an ignition plug 37, and a plurality of first, second, third, fourth and fifth air outlets … … which are sequentially arranged (a sixth air outlet is arranged in fig. 2), and the air outlets are respectively communicated with corresponding air nozzles on the nozzle disc 32 through respective air pipes 11, 12, 13, 14, 15 and 16. In the general arrangement of a gas turbine, the compressed air outlet 55 of the compressor 9 communicates with the scavenge inlet 31 on the rotor casing 28, and the scavenge outlet 7 on the rear side of the rotor casing 28 opens into the turbine 25. When the rotor 41 rotates with the turbine 25, the combustion chambers 45 of the sequentially rotated rotors are rotated to the positions of the ventilation inlet 31 and the ventilation outlet 7, and the ventilation inlet and the ventilation outlet on the rotor shell are communicated simultaneously, so that the compressed air discharged by the compressor 9 can extrude the working gas with the reduced pressure in the combustion chambers 45. A nozzle plate 32 is arranged at the front side of the turbine 25, a gas distribution angle area 40 '(refer to the attached drawing of the patent specification of a rotor supercharged gas turbine with the application number of 202010650212. X) which is the same as and corresponds to the plurality of gas distribution angle areas 40 on the rotor shell 28 is also divided on the nozzle plate, after a gas exchange outlet 7, a first gas outlet, a second gas outlet, a third gas outlet, a fourth gas outlet and a fifth gas outlet … … which are arranged in each of the plurality of gas distribution angle areas 40 on the rotor shell 28 are respectively arranged along respective gas transmission pipes in a deflection way, the gas exchange outlet, the fifth gas nozzle … …, the third gas nozzle, the first gas nozzle, the second gas nozzle and the fourth gas nozzle … … are sequentially arranged and communicated with each gas distribution angle area 40' on the nozzle plate 32 in the following order, so that the first gas outlet 1 on the rotor shell 28 is arranged and communicated with the gas outlets with the pressure gradually reduced from the maximum pressure, after the other end of the air pipe is connected to the nozzle plate 32 in a deflection arrangement, the air pipe becomes a first air nozzle which is communicated with the first air outlet and is a maximum pressure air nozzle with the middle position, and then the pressing force of the other corresponding air nozzles is sequentially arranged towards the left side and the right side of the first air nozzle in a descending order.
In order to increase the air capacity of the combustion chambers in the rotor supercharged gas turbine according to the present invention, as shown in fig. 1, in addition to the first row of combustion chambers 45 provided on the circumferential surface of the rotor 41, a second row of combustion chambers 45' and a third row of combustion chambers 45 ″ are additionally provided in the turbine side direction at a predetermined distance from the first row of combustion chambers. It is also possible to continue to add more rows of combustors as needed to meet the gas turbine air-transfer requirements at higher air flow rates. After the plurality of rows of combustion chambers are added to the rotor, the rotor casing 28 is also provided with a purge inlet 31, a second purge inlet 31 ', and a third purge inlet 31 ″, … … on the compressor side, and a purge outlet 7, a second purge outlet 7', and a third purge outlet 7 ″, … … on the turbine side, which are capable of communicating with the first row of combustion chambers, the second row of combustion chambers, and the third row of combustion chambers … …, respectively. The air delivery pipes 68 from the compressed air outlet 55 of the compressor 9 are respectively communicated with the corresponding air exchange inlet 31, the second air exchange inlet 31 ' and the third air exchange inlet 31 "on the rotor shell 28 through a first air inflation manifold 43, a second air inflation manifold 43 ' and a third air inflation manifold 43", the air exchange outlet 7, the second air exchange outlet 7 ' and the third air exchange outlet 7 "on the rotor shell are respectively communicated with the corresponding air exchange air delivery pipes 17 through a respective first air outlet manifold 44, a respective second air outlet manifold 44 ' and a respective third air outlet manifold 44", and the air delivery pipes are further communicated with the air exchange nozzles in the corresponding air distribution angular region 40 ' on the nozzle plate 32.
In correspondence with the first row of combustion chambers 45, the second row of combustion chambers 45 ' and the third row of combustion chambers 45 "of the rotor 41, as shown in fig. 3, the injection chamber 34, the second injection chamber 34 ' and the third injection chamber 34" are provided with the injector 35, and then the ignition chamber 36, the second ignition chamber 36 ' and the third ignition chamber 36 "are provided with the ignition plug 37, as shown in fig. 4. In order to make the first row of combustion chambers 45, the second row of combustion chambers 45' and the third row of combustion chambers 45 ″ on the rotor 41 communicate with the first air outlet, the second air outlet, the third air outlet, the fourth air outlet, the fifth air outlet and the sixth air outlet arranged behind the ignition cavity 36 on the rotor shell 28 in sequence, each air outlet on the rotor shell 28 is made into a corresponding number of small air outlets 24 (see fig. 5) to communicate with the rows of combustion chambers on the rotor 41, or each air outlet on the rotor shell is made into a long air outlet 42 (see fig. 8) to communicate with the rows of combustion chambers on the rotor, and then each group of air outlets are arranged along the respective air delivery pipe in a shifted manner and then communicate with the corresponding air outlets on the nozzle plate 32 to the turbine 25.
As shown in fig. 5, after each of the air outlets of the rotor shell 28 is made into a corresponding number of small air outlets 24 to communicate with the rows of combustion chambers on the rotor simultaneously, each small air outlet 24 is communicated with a corresponding air delivery pipe through a respective air delivery manifold 64, an air delivery two manifold 64' and an air delivery three manifold 64 ″, and the other end of each corresponding air delivery pipe is communicated with a corresponding air jet on the jet disk 32 after being arranged in a shifted manner. In fig. 5, after the first air outlet of the original gas turbine is replaced by three small air outlets 24, the three small air outlets are respectively communicated with corresponding air delivery pipes 11 through respective air outlet manifolds 64, air outlet two manifolds 64 'and air outlet three manifolds 64 ″, and the other ends of the air delivery pipes 11 are further communicated with corresponding air injection ports 1' on the nozzle plate 32. In fig. 2, the original first air outlet, second air outlet, third air outlet, fourth air outlet, fifth air outlet and sixth air outlet on the rotor shell 28 are respectively communicated with the corresponding air nozzles on the nozzle plate 32 through the respective air delivery pipes 11, 12, 13, 14, 15 and 16 after passing through the respective small air outlet 24, the air delivery manifold 64, the second air delivery manifold 64' and the third air delivery manifold 64 ″.
Because the pressure of the combustion chambers in the rotor decreases once after the combustion chambers rotate through one gas outlet, in order to reduce the pressure fluctuation when the combustion chambers in the rotor are communicated with the corresponding small gas outlets, as shown in fig. 6, in each group of small gas outlets 24 sequentially communicated with the corresponding gas conveying pipes on the rotor shell 28, the first small gas outlet 24 connected with the gas outlet manifold 64 is taken as a reference, each small gas outlet 24 at the later position is staggered with a certain angle relative to the small gas outlet at the front along the rotation direction (or the reverse direction) of the rotor, but the total staggered angle of the small gas outlets 24 is smaller than the angle occupied by one combustion chamber 45 (drawn by a dotted line) on the rotor. In practice, if the circumferential distance between the small air outlets 24 is too small to be beneficial to the structural strength of the rotor housing 28, the small air outlets 24 may be staggered in every other set in a manner of advancing toward the compressor.
If each set of small air outlets 24 of the air outlets on the rotor housing 28 is aligned with the central axis, as shown in fig. 7, each row of combustion chambers of the first row of combustion chambers 45, the second row of combustion chambers 45', and the third row of combustion chambers 45 "(dashed lines) on the rotor 41 may be inclined or staggered by a certain angle with respect to the combustion chambers of the front row along the rotation direction (or reverse direction) of the rotor, but the total inclined or staggered angle of the inclined or staggered combustion chambers is smaller than the angle occupied by one small air outlet 24 on the rotor housing 28. The three rows of combustion chambers in fig. 7 are arranged at an angle inclined in the direction of rotation of the rotor.
In order to make each air outlet on the rotor shell 28 communicate with the first row of combustion chambers 45, the second row of combustion chambers 45' and the third row of combustion chambers 45 ″ on the rotor, besides the three small air outlet structure in fig. 5, the structure arrangement shown in fig. 8 can be adopted, in the rotor shell structure in fig. 8, a long air outlet 42 which can communicate with a plurality of rows of combustion chambers on the rotor is formed by a long concave air outlet cavity 49 arranged on the inner wall of the rotor shell 28, each air outlet cavity 49 is communicated with a corresponding first air delivery pipe, a second air delivery pipe, a third air delivery pipe, a fourth air delivery pipe and a fifth air delivery pipe … … through a corresponding air outlet close to the turbine side, and the other end of each air delivery pipe is communicated with a corresponding air jet port on the nozzle plate 32 after being arranged in a shifted position. In fig. 8, after the first air outlet of the original gas turbine is replaced by the long air outlet 42 arranged on the inner wall of the rotor shell 28, the long air outlet is communicated with the air delivery pipe 11 through the air outlet 76 on the air outlet cavity 49, and the other end of the air delivery pipe 11 is communicated with the corresponding air jet 1' on the nozzle disk 32, so that the working gas jetted from the air jet can drive the following turbine 25 to rotate to work. In practice, if the spacing between the air outlets 76 in the air outlet cavity 49 is too small to be easily arranged, every other air outlet 76 can be staggered.
In order to reduce the pressure fluctuation occurring when the rows of combustion chambers are connected to the corresponding elongated outlet 42, as shown in fig. 9, each elongated outlet 42 of the rotor housing 28 is inclined at a certain angle in the direction of rotation (or in the reverse direction) of the rotor, but the total inclined angle occupies a width smaller than the opening angle width of the combustion chamber 45 (shown by a dotted line) on the rotor.
If the elongated air outlets 42 of the rotor housing 28 are aligned with the central axis, as shown in fig. 10, the combustion chambers of the first row 45, the second row 45', and the third row 45 "(dashed lines) of combustion chambers of the rotor may be inclined or staggered at a certain angle with respect to the combustion chambers of the front row along the direction (or reverse direction) of the rotation of the rotor, but the total angle of inclination or staggering of the combustion chambers is smaller than the opening angle of one elongated air outlet 42 of the rotor housing 28. The three rows of combustion chambers in fig. 10 are arranged at an angle inclined in the direction of rotation of the rotor.
In practice, to facilitate adjustment of the gap distance between the rotor and the rotor housing, as shown in fig. 1, after the rotor 41 and the corresponding rotor housing 28 are formed into a truncated cone shape, the rotor 41 formed into a truncated cone shape is mounted on a shaft drum 75 on the shaft 23 passing through the rotor by using a sliding sleeve structure, so that the rotor 41 can be adjusted to a small diameter side of the rotor housing and then fixed.
On the connecting shell 30 between the rotor 41 and the turbine 25, a connecting vent pipe 70 is provided, the other end of the connecting vent pipe is communicated with the vent hole 10 on the turbine shell 22 at the corresponding position behind the first stage turbine 26 or the second stage turbine 27, and the position of the vent hole is at the position of minimum airflow pressure in the turbine shell 22, so that the gas leaked in the connecting shell 30 can be timely discharged to the turbine side.
A connecting vent pipe 71 is arranged on a connecting shell 73 between the rotor 41 and the compressor 9, and the other end of the connecting vent pipe is communicated with a vent hole 74 on a compressor shell 72 at a position with slightly lower pressure, so that the gas leaked in the connecting shell 73 is discharged to the compressor side and then is pressed into a combustion chamber by the compressor to participate in circulating combustion.
Claims (10)
1. A rotor supercharged gas turbine comprises a gas compressor (9), a turbine (25) connected through a crankshaft (23), a rotor (41) arranged between the gas compressor (9) and the turbine (25), the rotor is arranged in a rotor shell (28), a plurality of pit type combustion chambers (45) with the same shape and the same interval distance are densely arranged on the rotor (41) in the circumferential direction, two or more than two equal gas distribution angle areas (40) are divided on the rotor shell (28), a gas exchange inlet (31) and a gas exchange outlet (7) which are positioned in the same angle, a gas injection cavity (34) provided with a fuel injector (35), an ignition cavity (36) provided with a spark plug (37) and a plurality of first gas outlets which are sequentially arranged from the initial position of each gas distribution angle area (40) on the rotor shell (28) to the tail end position in the rotating direction of the rotor (41) and correspond to the positions of the combustion chambers (45) on the rotor, A compressed air outlet (55) of the air compressor (9) is communicated with a ventilation inlet (31) on the rotor shell (28), a ventilation outlet (7) on the rear side of the rotor shell (28) leads to the turbine (25), when the rotor (41) rotates along with the turbine (25), a combustion chamber (45) on the rotor which is sequentially turned over can simultaneously communicate the ventilation inlet and the ventilation outlet on the rotor shell when the rotor rotates to the positions of the ventilation inlet (31) and the ventilation outlet (7), a nozzle disc (32) is arranged on the front side of the turbine (25), a gas distribution angle area (40') which is the same as and corresponds to a plurality of gas distribution angle areas (40) on the rotor shell (28) is also divided on the nozzle disc, and ventilation outlets (7) arranged on the plurality of gas distribution angle areas (40) on the rotor shell (28), The first air outlet, the second air outlet, the third air outlet, the fourth air outlet and the fifth air outlet … … are arranged along the respective air conveying pipes by displacement, then the air distribution angle area (40') on the nozzle plate (32) is sequentially communicated with a ventilation nozzle, … … a fifth air nozzle, a third air nozzle, a first air nozzle, a second air nozzle and a fourth air nozzle (… …) in the following sequence, so that the first air outlet (1) on the rotor shell (28) is arranged from the maximum pressure to the gradually reduced pressure, and is connected to the nozzle plate (32) through the displacement arrangement of the other end of the air pipe, become the maximum pressure gas port that is the intermediate position with the first air vent of first gas outlet intercommunication, arrange respectively its characterized in that to the left and right sides of first air vent in proper order to each other air vent pressing force decrement order of corresponding again: in addition to the first row of combustion chambers (45) being provided on the circumferential surface of the rotor (41), a second row of combustion chambers (45 ') and a third row of combustion chambers (45') … … are additionally provided in the turbine-side direction at a predetermined distance from the first row of combustion chambers, and correspondingly, a compressor-side ventilation inlet (31), a second ventilation inlet (31 '), and a third ventilation inlet (31') … …, which are capable of communicating with the first row of combustion chambers, the second row of combustion chambers, and the third row of combustion chambers … …, and a compressor-side ventilation outlet (7), a second ventilation outlet (7 '), and a third ventilation outlet (7') … … are also provided on the rotor case (28), and each of the ventilation passages (68) connected from the compressed air outlet port (55) of the compressor (9) is connected to the corresponding ventilation inlet (31) of the rotor case (28) through a first manifold charge air pipe (43), a second charge air manifold (43 '), and a third charge air manifold (43' … …), respectively, The second ventilation inlet (31 ') and the third ventilation inlet (31 ') … … are communicated, the ventilation outlet (7), the second ventilation outlet (7 ') and the third ventilation outlet (7 ') … … on the rotor shell are respectively communicated with corresponding ventilation air conveying pipes (17) through a first air outlet manifold (44), a second air outlet manifold (44 ') and a third air outlet manifold (44 ') … …, and the air conveying pipes are communicated with the ventilation nozzles in the corresponding air distribution angle area (40 ') on the nozzle plate (32); corresponding to a first row of combustion chambers (45), a second row of combustion chambers (45 ') and a third row of combustion chambers (45') … … on the rotor (41), an injection cavity (34) provided with an injector (35), a second injection cavity (34 ') and a third injection cavity (34') … … are correspondingly arranged on the rotor shell (28), and then an ignition cavity (36) provided with an ignition plug (37), a second ignition cavity (36 ') and a third ignition cavity (36') … … are correspondingly arranged; in order to enable a first row of combustion chambers (45), a second row of combustion chambers (45 ') and a third row of combustion chambers (45') … … on the rotor (41) to be communicated with a first air outlet, a second air outlet, a third air outlet, a fourth air outlet and a fifth air outlet … … which are arranged in sequence behind an ignition cavity on a rotor shell (28), each air outlet on the rotor shell is made into a corresponding number of small air outlets (24) to be communicated with a plurality of rows of combustion chambers on the rotor, or each air outlet on the rotor shell is made into a long air outlet (42) to be communicated with a plurality of rows of combustion chambers on the rotor, and then each group of air outlets are arranged in a shifted way through respective air conveying pipes and are communicated with corresponding air injection ports on a nozzle disc (32) to a turbine (25).
2. The rotorcraft gas turbine of claim 1, wherein: after each air outlet of each air outlet on the rotor shell (28) is made into a corresponding number of small air outlets (24) to be communicated with the plurality of rows of combustion chambers on the rotor simultaneously, each small air outlet (24) is communicated with a corresponding air delivery pipe through a respective air delivery manifold (64), an air delivery two manifold (64 ') and an air delivery three manifold (64'), and the other end of each corresponding air delivery pipe is communicated with a corresponding air jet on the jet disc (32) after being arranged in a deflection way.
3. The rotorcraft gas turbine of claim 2, wherein: in each group of small air outlets (24) which are sequentially communicated with the corresponding air conveying pipes on the rotor shell (28), the first small air outlet (24) connected with the air outlet manifold (64) is taken as a reference, each small air outlet (24) at the later position is staggered by a certain angle relative to the small air outlet at the front along the rotation direction (or the reverse direction) of the rotor, but the total staggered angle of the small air outlets (24) is smaller than the angle occupied by one combustion chamber (45) on the rotor.
4. The rotorcraft gas turbine of claim 2, wherein: when each group of small air outlets (24) of the air outlets on the rotor shell (28) is aligned with the central axis, in a first row of combustion chambers (45), a second row of combustion chambers (45 ') and a third row of combustion chambers (45') … … on the rotor (41), each row of combustion chambers can be inclined or staggered at a certain angle relative to the combustion chambers in the front row along the rotation direction (or the reverse direction) of the rotor, but the total inclined or staggered angle of the inclined or staggered combustion chambers is smaller than the angle occupied by one small air outlet (24) on the rotor shell (28).
5. The rotorcraft gas turbine of claim 1, wherein: the long air outlets (42) which can be communicated with a plurality of rows of combustion chambers on the rotor are formed by long pit air outlet cavities (49) arranged on the inner wall of the rotor shell (28), each air outlet cavity (49) is communicated with a corresponding first air conveying pipe, a corresponding second air conveying pipe, a corresponding third air conveying pipe, a corresponding fourth air conveying pipe and a corresponding fifth air conveying pipe … … through a corresponding air outlet close to the turbine side, and the other end of each air conveying pipe is communicated with a corresponding air jet on the jet disc (32) after being arranged in a deflection way.
6. The rotorcraft gas turbine of claim 5, wherein: each long air outlet (42) on the rotor shell (28) is arranged in a certain inclined angle along the rotation direction (or the reverse direction) of the rotor, but the total inclined angle occupies a width smaller than the opening angle width of a combustion chamber on the rotor (41).
7. The rotorcraft gas turbine of claim 5, wherein: when the long air outlets (42) on the rotor shell (28) are aligned with the central axis, the combustion chambers in the first row (45), the second row (45 ') and the third row (45') … … on the rotor (41) can be inclined or staggered at a certain angle relative to the combustion chambers in the front row along the rotation direction (or reverse direction) of the rotor, but the total inclined or staggered angle of the combustion chambers is smaller than the opening angle of one long air outlet (42) on the rotor shell (28).
8. The rotorcraft gas turbine of claim 1, 2, or 5, wherein: the rotor (41) is made into a truncated cone-shaped sliding sleeve structure and is arranged on a shaft drum (75) of a machine shaft (23) penetrating through the rotor, so that the rotor (41) can be adjusted to a small diameter side of a rotor shell and then fixed.
9. The rotorcraft gas turbine of claim 1, 2, or 5, wherein: a connecting vent pipe (70) is arranged on a connecting shell (30) between the rotor (41) and the turbine (25), the other end of the connecting vent pipe is communicated with a vent hole (10) on the turbine shell (22) at the corresponding position behind the first-stage turbine (26) or the second-stage turbine (27), and the position of the vent hole is at the position with the minimum airflow pressure in the turbine shell (22).
10. The rotorcraft gas turbine of claim 1, 2, or 5, wherein: a connecting vent pipe (71) is arranged on a connecting shell (73) between the rotor (41) and the compressor, and the other end of the connecting vent pipe is communicated with a vent hole (74) on a compressor shell (72) at a position with slightly lower pressure.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010847769.2A CN111963313A (en) | 2020-08-21 | 2020-08-21 | Rotor supercharging gas turbine |
| PCT/CN2021/000174 WO2022036996A1 (en) | 2020-08-21 | 2021-08-18 | Rotor supercharged gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010847769.2A CN111963313A (en) | 2020-08-21 | 2020-08-21 | Rotor supercharging gas turbine |
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| Publication Number | Publication Date |
|---|---|
| CN111963313A true CN111963313A (en) | 2020-11-20 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010847769.2A Pending CN111963313A (en) | 2020-08-21 | 2020-08-21 | Rotor supercharging gas turbine |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN111963313A (en) |
| WO (1) | WO2022036996A1 (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113357197A (en) * | 2021-07-13 | 2021-09-07 | 浙江燃创透平机械股份有限公司 | Gas turbine that makes things convenient for adjustment holds ring fixed knot and constructs |
| WO2022036996A1 (en) * | 2020-08-21 | 2022-02-24 | 韩培洲 | Rotor supercharged gas turbine |
| WO2022073310A1 (en) * | 2020-10-09 | 2022-04-14 | 韩培洲 | Rotor supercharged-type gas turbine |
| WO2023241021A1 (en) * | 2022-06-14 | 2023-12-21 | 韩培洲 | Gas jet stream splitting-type rotor supercharged gas turbine |
| WO2024001147A1 (en) * | 2022-07-01 | 2024-01-04 | 韩培洲 | Ventilation control system of rotor supercharged gas turbine |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2844551A1 (en) * | 2002-09-17 | 2004-03-19 | Emile Weisman | Rotary internal combustion engine for motor vehicle has two stage turbine to draw air into combustion chamber and extract power from exhaust gases |
| CN102251851B (en) * | 2011-06-15 | 2012-10-10 | 毛中义 | Turbine rotor engine |
| CN202091036U (en) * | 2011-06-15 | 2011-12-28 | 毛中义 | Turbine rotor engine |
| CN108625985A (en) * | 2017-03-23 | 2018-10-09 | 迟多功 | Positive-pressure type gas turbine |
| CN207437204U (en) * | 2017-08-21 | 2018-06-01 | 迟多功 | Hybrid gas turbine |
| CN111075564B (en) * | 2019-12-27 | 2022-10-28 | 孙金良 | Turbine rotor engine |
| CN111963313A (en) * | 2020-08-21 | 2020-11-20 | 韩培洲 | Rotor supercharging gas turbine |
| CN112145294A (en) * | 2020-10-09 | 2020-12-29 | 韩培洲 | Rotor supercharged gas turbine |
-
2020
- 2020-08-21 CN CN202010847769.2A patent/CN111963313A/en active Pending
-
2021
- 2021-08-18 WO PCT/CN2021/000174 patent/WO2022036996A1/en active Application Filing
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2022036996A1 (en) * | 2020-08-21 | 2022-02-24 | 韩培洲 | Rotor supercharged gas turbine |
| WO2022073310A1 (en) * | 2020-10-09 | 2022-04-14 | 韩培洲 | Rotor supercharged-type gas turbine |
| CN113357197A (en) * | 2021-07-13 | 2021-09-07 | 浙江燃创透平机械股份有限公司 | Gas turbine that makes things convenient for adjustment holds ring fixed knot and constructs |
| WO2023241021A1 (en) * | 2022-06-14 | 2023-12-21 | 韩培洲 | Gas jet stream splitting-type rotor supercharged gas turbine |
| WO2024001147A1 (en) * | 2022-07-01 | 2024-01-04 | 韩培洲 | Ventilation control system of rotor supercharged gas turbine |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2022036996A1 (en) | 2022-02-24 |
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