Turbine structure with high expansion ratio

Abstract

A high-expansion-ratio turbine structure is characterized by comprising a volute body and a turbine rotor. The turbine rotor comprises a turbine shaft, a plurality of high-pressure rotor blades, a plurality of low-pressure rotor blades and a blade partition plate, one end of the turbine shaft extends into the volute body, and the other end of the turbine shaft extends into the gas compressor; the top of the end, extending into the volute body, of the turbine shaft is the upper end, and a low-pressure rotor blade, an air cavity partition plate and a high-pressure rotor blade are sequentially arranged from top to bottom. The high-pressure rotor blades and the low-pressure rotor blades are in mirror symmetry by taking the blade partition plates as boundaries, and are circumferentially and uniformly distributed on the outer side wall of the turbine shaft by taking the axis of the turbine shaft as a circle center; the turbine structure can effectively improve the exhaust energy utilization rate of the engine, improve the expansion ratio of the turbine rotor and increase the expansion work of the turbine rotor, namely increase the work of a gas compressor, so that the power and economical efficiency of the engine can be greatly improved.

Description

Technical Field

[0001] The invention relates to the technical field of exhaust gas turbochargers, in particular to a high expansion ratio turbine structure. Background Art

[0002] The exhaust gas turbocharger uses the exhaust gas energy of the engine to drive the turbine in the volute to rotate. The turbine drives the coaxial compressor impeller to work. Fresh air enters the compressor through the air filter. The compressor impeller rotates to compress the fresh air to achieve the supercharging effect. Therefore, the exhaust gas turbocharger can effectively recycle the exhaust gas energy, increase the air volume in the cylinder under the same displacement, optimize the combustion process, and improve the working efficiency of the internal combustion engine. It is an indispensable component for the engine to increase power, save fuel and reduce consumption, and improve emissions.

[0003] With the upgrading of emission regulations and the tension of energy resources, the technical requirements for automotive superchargers are further improved. In order to meet the National VI B and even National VII emission requirements, various OEMs have proposed to optimize the combustion process, improve the utilization rate of exhaust capacity, and thus improve the working efficiency of the engine. Compared with the traditional single-channel volute, the double-channel volute can establish higher turbine pre-turbine temperature and pre-turbine pressure through separate exhaust control of the double-channel under the same intake conditions, effectively improve the utilization rate of exhaust capacity and improve the overall emission.

[0004] Existing turbocharger turbine rotors (such as Figure 1 (As shown) Generally, only one side of the turbine rotor back plate is equipped with turbine blades, and the exhaust gas has only one-stage expansion, the expansion ratio is relatively low, and the exhaust gas energy utilization rate is low. With the continuous increase in engine performance requirements, the performance of turbochargers is required to be continuously improved. The traditional turbochargers with blades on one side are currently used. Due to the low expansion ratio and low exhaust gas energy utilization rate, it is becoming increasingly difficult to meet the use requirements, and there is a bottleneck in performance improvement. Therefore, designing a high expansion ratio turbocharger will become one of the main development directions of turbochargers in the future. Summary of the invention

[0005] The purpose of the present invention is to overcome the deficiencies of the prior art and to provide a high expansion ratio turbine structure that can effectively improve the turbine expansion ratio, overcome the current bottleneck in improving turbine performance, improve the utilization rate of exhaust gas kinetic energy, and increase the overall working efficiency of the turbine.

[0006] The technical solution of the present invention is: a high expansion ratio turbine structure, characterized in that it includes a volute body and a turbine rotor; The turbine rotor comprises a turbine shaft, a plurality of high-pressure rotor blades, a plurality of low-pressure rotor blades and a blade partition. One end of the turbine shaft extends into the volute body, and the other end extends into the compressor. The top of one end of the turbine shaft extending into the volute body is the upper end, and from top to bottom are the low-pressure rotor blades, the air cavity partition and the high-pressure rotor blades. The high-pressure rotor blades and the low-pressure rotor blades are in a mirror-symmetrical relationship with the blade partition as the boundary, and are evenly distributed in a circle with the turbine shaft axis as the center on the outer wall of the turbine shaft. The volute body is divided into a high-pressure air chamber and a low-pressure exhaust chamber by the blade partition. A high-pressure air inlet connected to the exhaust gas outlet of the engine combustion chamber is provided on the side wall of the high-pressure air chamber, and a low-pressure air inlet is provided on the side wall of the low-pressure exhaust chamber at a position opposite to the high-pressure air inlet. An exhaust flow channel is provided at the bottom of the high-pressure air chamber, and the exhaust flow channel is connected to the low-pressure air inlet through a connecting pipe.

[0007] The working principle of the present invention is: the inner cavity of the volute body is divided into a high-pressure air chamber and a low-pressure exhaust chamber by using a blade partition. When the supercharger is running, the engine exhaust flows into the high-pressure air chamber from the high-pressure air inlet, works on the high-pressure rotor blades to drive the turbine shaft to rotate, and the low-grade pressurized gas after one expansion and work passes through the exhaust flow channel, flows into the low-pressure exhaust chamber through the low-pressure air inlet, further works on the low-pressure rotor blades, further drives the turbine shaft to rotate faster, and is finally discharged from the low-pressure exhaust chamber to the exhaust pipe.

[0008] Compared with the prior art, the present invention has the following advantages: the turbine structure can effectively improve the utilization rate of engine exhaust energy, increase the turbine rotor expansion ratio, increase the turbine rotor expansion work, that is, increase the compressor work, thereby greatly improving the engine power and economy.

[0009] The present invention is further described below in conjunction with the figures and embodiments. BRIEF DESCRIPTION OF THE DRAWINGS

[0010] Figure 1 It is a schematic diagram of the structure of the existing turbine rotor of the present invention; Figure 2 It is a schematic diagram of the structure of an embodiment of the present invention; Figure 3 for Figure 2 Schematic diagram of the airway structure. DETAILED DESCRIPTION Example

[0011] As shown in the figure, a high expansion ratio turbine structure is characterized by comprising a volute body 1 and a turbine rotor 2; The turbine rotor 2 comprises a turbine shaft 21, a plurality of high-pressure rotor blades 22, a plurality of low-pressure rotor blades 23 and a blade partition 24. One end of the turbine shaft 21 extends into the volute body 1, and the other end extends into the compressor (not shown); the top of one end of the turbine shaft 21 extending into the volute body 1 is the upper end, and from top to bottom are the low-pressure rotor blades 23, the air cavity partition 24 and the high-pressure rotor blades 22; the high-pressure rotor blades 22 and the low-pressure rotor blades 23 are in a mirror-symmetrical relationship with the blade partition 24 as the boundary, and are evenly distributed in a circle with the axis of the turbine shaft 21 as the center on the outer wall of the turbine shaft 21; The volute body 1 is divided into a high-pressure air chamber 11 and a low-pressure exhaust chamber 12 by the blade partition 24. A high-pressure air inlet 13 connected to the exhaust gas outlet of the engine combustion chamber is provided on the side wall of the high-pressure air chamber 11, and a low-pressure air inlet 14 is provided on the side wall of the low-pressure exhaust chamber 12 at a position opposite to the high-pressure air inlet 13. An exhaust flow channel 15 is provided at the bottom of the high-pressure air chamber 11, and the exhaust flow channel 15 is connected to the low-pressure air inlet 13 through a connecting pipe.

[0012] The inner cavity of the volute body 1 is divided into a high-pressure air chamber 11 and a low-pressure exhaust chamber 12 by a blade partition 24. When the supercharger is running, the engine exhaust flows into the high-pressure air chamber 11 from the high-pressure air inlet 13, works on the high-pressure rotor blades 22, and drives the turbine shaft 21 to rotate. After one expansion and work, the low-grade pressurized gas passes through the exhaust flow channel 15 and flows into the low-pressure exhaust chamber 12 through the low-pressure air inlet 13, further works on the low-pressure rotor blades 23, further drives the turbine shaft 21 to rotate faster, and is finally discharged from the low-pressure exhaust chamber 12 to the exhaust pipe (not shown).

Claims

1. A high expansion ratio turbine structure, characterized in that It includes a volute body and a turbine rotor; The turbine rotor comprises a turbine shaft, a plurality of high-pressure rotor blades, a plurality of low-pressure rotor blades and a blade partition. One end of the turbine shaft extends into the volute body, and the other end extends into the compressor. The top of one end of the turbine shaft extending into the volute body is the upper end, and from top to bottom are the low-pressure rotor blades, the air cavity partition and the high-pressure rotor blades. The high-pressure rotor blades and the low-pressure rotor blades are in a mirror-symmetrical relationship with the blade partition as the boundary, and are evenly distributed in a circle with the turbine shaft axis as the center on the outer wall of the turbine shaft. The volute body is divided into a high-pressure air chamber and a low-pressure exhaust chamber by the blade partition. A high-pressure air inlet connected to the exhaust gas outlet of the engine combustion chamber is provided on the side wall of the high-pressure air chamber, and a low-pressure air inlet is provided on the side wall of the low-pressure exhaust chamber at a position opposite to the high-pressure air inlet. An exhaust flow channel is provided at the bottom of the high-pressure air chamber, and the exhaust flow channel is connected to the low-pressure air inlet through a connecting pipe.

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