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CN-121993436-A - Compressor, supercharger and engine

CN121993436ACN 121993436 ACN121993436 ACN 121993436ACN-121993436-A

Abstract

The application provides a compressor, a supercharger and an engine. The compressor includes a compressor housing having an impeller chamber, an impeller rotatably disposed within the impeller chamber, the impeller including a hub and a blade assembly connected, at least one blade of the blade assembly configured such that a leading edge of the blade has a meridional forward sweep angle relative to a radial line of the hub. The front edge of the blade adopts a forward-swept design, so that the leakage vortex intensity of the tip of the blade can be reduced, the airflow excitation intensity is reduced, the surge margin is improved, the intake charge is improved, the flow loss is reduced, the efficiency is improved, and the energy consumption is reduced, thereby ensuring that the compressor can improve the efficiency of braking a thermal efficiency point under the condition of low pressure ratio (for example, the pressure ratio is within the range of 1.5) while maintaining good surge margin, improving the overall fuel consumption performance, improving the aerodynamic performance and the stability of the compressor, and ensuring that the compressor can operate with high efficiency.

Inventors

  • LI XIAODONG
  • LI PENGNIAN
  • ZHANG ZHICHAO

Assignees

  • 盖瑞特动力科技(上海)有限公司
  • 盖瑞特动力科技(武汉)有限公司

Dates

Publication Date
20260508
Application Date
20260408

Claims (10)

  1. 1. A gas compressor, which comprises a gas compressor, characterized by comprising the following steps: a compressor housing having an impeller chamber; an impeller rotatably disposed within the impeller chamber; The impeller comprises a hub and a blade assembly which are connected; At least one blade of the blade assembly is configured such that a leading edge of the blade has a meridional forward sweep angle relative to a radial line of the hub.
  2. 2. The compressor of claim 1, wherein the impeller has a hub ratio of not less than 0.3 and not more than 0.45.
  3. 3. The compressor of claim 1, wherein the meridional forward sweep is greater than 0 ° and no greater than 30 °.
  4. 4. The compressor of claim 1, wherein the vane assembly includes a plurality of main vanes; The plurality of main blades are sequentially arranged on the periphery of the hub along the circumferential direction of the hub; At least one of the leading edges of the main blades is gradually closer to the air inlet end of the compressor housing in a radial direction gradually away from the hub.
  5. 5. The compressor of claim 4, wherein a ratio of an area of an outlet region to an area of an inlet region of the impeller is proportional to a diameter of the impeller outlet and a width of the impeller outlet in an axial direction, and inversely proportional to a square difference between an outer diameter of a leading edge of the main blade and a diameter of the hub at a junction with the leading edge of the main blade.
  6. 6. The compressor of claim 5, wherein a ratio of an area of an outlet region to an area of an inlet region of the impeller is not less than 85% and not more than 98%.
  7. 7. The compressor of claim 5, wherein the discharge area of the impeller is an integer multiple of the discharge area between adjacent two of the main blades.
  8. 8. The compressor of claim 4, wherein said vane assembly further comprises a plurality of splitter vanes; the splitter blades are arranged between two adjacent main blades and are close to the outlets of the main blades; the leading edge of at least one of the splitter blades is gradually closer to the air inlet end of the compressor housing in a radial direction gradually away from the hub.
  9. 9. A kind of booster, which is used to boost the pressure of the air, characterized by comprising the following steps: the compressor of any one of claims 1 to 8.
  10. 10. An engine comprising a compressor according to any one of claims 1 to 8.

Description

Compressor, supercharger and engine Technical Field The application relates to the technical field of compressors, in particular to a compressor, a supercharger and an engine. Background A compressor (compressor) is a component that applies work to air using blades rotating at a high speed to increase the pressure of the air. When the surge margin of the compressor meets the requirement, the working stability of the compressor is enhanced. The compressor can reduce energy consumption when a point efficiency (BTE) of the brake heat efficiency (brake THERMAL EFFICIENCY) of the engine satisfies a requirement. Braking thermal efficiency point efficiency is a core indicator for evaluating the conversion of fuel chemical energy (i.e., energy stored by fuel molecules through chemical bonds that can be released as thermal energy in a chemical reaction, such as combustion) into useful crankshaft output power (e.g., rotational torque output by a crankshaft). However, current compressors have smaller surge margins or lower efficiency at the BTE point. Disclosure of Invention Aiming at the defects of the existing mode, the application provides a compressor, a supercharger and an engine, which are used for solving the technical problems of smaller surge margin or lower efficiency at a BTE point in the related technology. In a first aspect, an embodiment of the present application provides a compressor, including: a compressor housing having an impeller chamber; The impeller is rotatably arranged in the impeller cavity; The impeller comprises a hub and a blade assembly which are connected; at least one blade of the blade assembly is configured such that the leading edge of the blade has a meridional forward sweep with respect to a radial line of the hub. Alternatively, the hub ratio of the impeller is not less than 0.3 and not more than 0.45. Optionally, the meridian forward sweep is greater than 0 ° and not greater than 30 °. Optionally, the blade assembly comprises a plurality of main blades; The plurality of main blades are sequentially arranged on the periphery of the hub along the circumferential direction of the hub; The leading edge of at least one main blade is gradually close to the air inlet end of the compressor housing along the radial direction gradually far away from the hub. Alternatively, the ratio of the area of the outlet region to the area of the inlet region of the impeller is proportional to the diameter of the impeller outlet and the width of the impeller outlet in the axial direction, and inversely proportional to the square difference between the outer diameter of the leading edge of the main blade and the diameter of the hub at the junction with the leading edge of the main blade. Optionally, the ratio of the area of the outlet region to the area of the inlet region of the impeller is not less than 85% and not more than 98%. Optionally, the area of the gas exit area of the impeller is an integer multiple of the area of the gas exit area between two adjacent main blades. Optionally, the blade assembly further comprises a plurality of splitter blades; The splitter blades are arranged between two adjacent main blades and are close to the outlets of the main blades; The leading edge of at least one splitter blade is gradually closer to the air inlet end of the compressor housing in a radial direction gradually away from the hub. In a second aspect, an embodiment of the present application provides a supercharger comprising a compressor as described above. In a third aspect, an embodiment of the present application provides an engine comprising a compressor as described above. The technical scheme provided by the embodiment of the application has the beneficial technical effects that: in an embodiment of the application, the compressor housing encloses an impeller chamber for accommodating the impeller. The impeller is disposed within the impeller chamber and is rotatable relative to the compressor housing. The rotating impeller serves to draw gas (e.g., ambient air) into the impeller chamber and accelerate and pre-pressurize the gas, thereby increasing the gas pressure and increasing the gas kinetic energy. The vane assembly of impeller is fixed to be set up on wheel hub, and wheel hub rotates and drives vane assembly rotation, can form the negative pressure in the impeller cavity to realize inhaling gas and accelerate and pre-boost to gas. The blade assembly includes a plurality of blades, a leading edge of at least one of the plurality of blades being swept forward, the leading edge of the at least one blade being swept forward forming a meridional forward sweep angle α with a radial line of the hub. In the embodiment of the application, the front edge of the blade adopts a forward-swept design, so that the leakage vortex intensity of the tip of the blade can be reduced, the airflow excitation intensity is reduced, the surge margin is improved, the intake charge is improved, the flow loss is reduce