Radial flow turbine with telescopic and adjustable nozzle blades

Abstract

The invention relates to a radial flow turbine with telescopic and adjustable nozzle blades. The radial flow turbine comprises a turbine box shell, turbine nozzle blades, turbine nozzle end wall supporting plates and an adjusting mechanism, wherein the turbine nozzle blades, the turbine nozzle end wall supporting plates and the adjusting mechanism are arranged in the turbine box shell. The turbine nozzle blade is of a nested combined structure capable of being deformed in a drawing mode, relative displacement between different nested layers of the combined nozzle blade is achieved through an adjusting mechanism, and telescopic deformation of the turbine nozzle blade is achieved. The turbine nozzle blade is formed by nesting an embedded trailing edge assembly and an externally-embedded blade body assembly, and after the blade is contracted, the relative position relation of the blade is a telescopic and adjustable radial flow turbine wrapping left and right. A plurality of nesting assemblies with limit limiting structures are utilized to form the turbine nozzle blade, and the nozzle blade is lengthened and shortened through the adjusting mechanism, so that the nozzle blade can be lengthened and shortened on the premise that the nozzle outlet airflow angle direction is not obviously changed and reverse adjustment of the attack angle of the rotary adjustable nozzle is avoided. Effective adjustment of the throat area of the nozzle is achieved, and the total pressure adjustment requirement of a turbine is met.

Description

Technical Field

[0001] The invention belongs to the technical field of power machinery, and in particular relates to a radial flow turbine with adjustable nozzle blade extension. Background Art

[0002] In the field of internal combustion engine research and development, exhaust gas turbocharging is a common technology used to improve the specific power and fuel economy of internal combustion engines and reduce exhaust gas and noise pollution. In a turbocharger, the turbine is the main core component of the turbocharger responsible for converting exhaust gas energy into mechanical energy and performing external work. Its working efficiency directly affects the performance of the turbocharger. In actual engineering, on the one hand, my country's geographical environment is highly diverse, and on the other hand, the high and low operating conditions of internal combustion engines are frequently switched during operation. The turbine intake conditions are complex and changeable during the operation of the turbocharger. It is difficult to maintain efficient operation in the entire working range using fixed nozzles or nozzleless solutions. The use of a rotary adjustable nozzle faces the problem of difficulty in matching the total pressure regulation requirements with the angle of attack regulation requirements. Summary of the invention

[0003] The present invention provides a radial flow turbine with adjustable nozzle blade extension, which can effectively adjust the nozzle throat area and meet the turbine total pressure regulation requirements without significantly changing the nozzle outlet airflow angle direction and avoiding reverse adjustment of the rotary adjustable nozzle attack angle.

[0004] In order to solve the above technical problems, the present invention provides a radial flow turbine with adjustable nozzle blades, characterized in that: it includes turbine nozzle blades; the turbine nozzle blades adopt a nested combination structure that can be pulled out and deformed to achieve the telescopic deformation of the turbine nozzle blades and adjust the nozzle throat area.

[0005] Furthermore, the turbine nozzle blade is composed of an embedded trailing edge component 2 and an embedded blade body component 3 which are nested.

[0006] Furthermore, after the turbine nozzle blades are retracted, the relative position relationship is that of a telescopic and adjustable radial flow turbine wrapped left and right.

[0007] Furthermore, both the embedded trailing edge assembly 2 and the embedded blade body assembly 3 are installed on the nozzle end wall 1 .

[0008] Furthermore, the externally embedded blade assembly 3 is fixedly connected to the nozzle end wall 1, and the internally embedded trailing edge assembly 2 is not fixedly connected to the nozzle end wall 1 and the externally embedded blade assembly 3, and can be relatively displaced relative to the fixing part formed by the nozzle end wall 1 and the externally embedded blade assembly 3.

[0009] Furthermore, on the connection surface between the nozzle end wall and the embedded trailing edge component 2, a groove and boss structure that fits together and does not affect relative displacement is processed according to actual needs to suppress leakage flow between the nozzle end wall 1 and the embedded trailing edge component 2.

[0010] Furthermore, when the supercharger can operate normally at high speed, the embedded trailing edge assembly 2 is completely retracted into the externally embedded blade assembly 3 to ensure that the nozzle throat flow area is sufficient to meet the high-speed operation requirements; when the supercharger intake energy is insufficient, the embedded trailing edge assembly 2 extends outward from the externally embedded blade assembly 3 as needed, thereby reducing the nozzle throat area, increasing the supercharger turbine pressure ratio, and improving the supercharger's working capacity.

[0011] Furthermore, the blade is composed of two or more nested components with limit limiting structures. The blade is extended by pulling different nested components through the adjusting mechanism, and the blade is shortened by pushing different nested components through the adjusting mechanism.

[0012] Furthermore, the relative position relationship of the open ends of the nested components of the combined nozzle blades after the blades are fully retracted is completely wrapped inside and outside or partially wrapped inside and outside; the adjustment mechanism is driven by electricity, magnetism, hydraulic pressure, air pressure or a combination of these.

[0013] Beneficial effect: The present invention utilizes a plurality of nested components with an extreme limiting structure to form turbine nozzle blades, and realizes the extension and shortening of the nozzle blades through an adjusting mechanism, thereby realizing effective adjustment of the nozzle throat area and meeting the turbine total pressure regulation requirements without significantly changing the nozzle outlet airflow angle direction and avoiding reverse adjustment of the rotary adjustable nozzle attack angle. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 It is a schematic diagram of the structure of the present invention. DETAILED DESCRIPTION

[0015] In order to make the purpose, content and advantages of the present invention more clear, the specific implementation methods of the present invention are further described in detail below.

[0016] The invention provides a radial flow turbine with adjustable nozzle blades, comprising a turbine housing, a turbine nozzle blade arranged in the turbine housing, a turbine nozzle end wall support plate and an adjustment mechanism;

[0017] The turbine nozzle blades adopt a nested combination structure that can be pulled out and deformed. The relative displacement between different nested layers of the combined nozzle blades is achieved through the adjustment mechanism, thereby achieving the telescopic deformation of the turbine nozzle blades.

[0018] The turbine nozzle blades are formed by nesting an embedded trailing edge component 2 and an embedded blade body component 3. After the blades are retracted, the relative position relationship is a telescopic and adjustable radial flow turbine wrapped left and right.

[0019] The exemplary embodiments and descriptions of the present invention are used to explain the present invention and do not constitute improper limitations on the present invention. In the figure, the blade is used to show the positional relationship of the two nested components when the combined blade is fully retracted, and the dotted line is used to show the positional relationship of the two nested components when the blade is partially stretched.

[0020] In actual applications, the two nested components, the embedded trailing edge component 2 and the embedded blade body component 3, are both installed on the nozzle end wall 1; wherein the embedded blade body component 3 and the nozzle end wall 1 are fixedly connected and cannot undergo relative displacement, and the embedded trailing edge component 2 is not fixedly connected to the nozzle end wall 1 and the embedded blade body component 3, and can undergo relative displacement relative to the fixing member formed by the nozzle end wall 1 and the embedded blade body component 3; on the connecting surface between the nozzle end wall 1 and the embedded trailing edge component 2, a groove boss structure that fits in with each other and does not affect the relative displacement is processed according to actual needs to suppress leakage flow between the nozzle end wall 1 and the embedded trailing edge component 2;

[0021] When the supercharger can operate normally at high speed, the embedded trailing edge assembly 2 is completely retracted into the externally embedded blade assembly 3 to ensure that the nozzle throat flow area is sufficient to meet the high-speed operation requirements; when the supercharger intake energy is insufficient, the embedded trailing edge assembly 2 extends outward from the externally embedded blade assembly 3 as needed, thereby reducing the nozzle throat area, increasing the supercharger turbine pressure ratio, and improving the supercharger's working capacity.

[0022] The blade can be composed of two or more nested components with limit limit structures, and the blade can be extended by pulling different nested components through the adjustment mechanism, and the blade can be shortened by pushing different nested components through the adjustment mechanism;

[0023] Combined nozzle blades, the number of nested components of a single blade can be 2 or more, one or more components can be directly connected to the adjustment mechanism, and one nested component can be directly connected to a fixed component such as a turbine nozzle end wall support plate;

[0024] The relative positional relationship of the nested components of the combined nozzle blades at the pulled-out opening end after the blades are fully retracted, including but not limited to complete inner-outer wrapping and partial inner-outer wrapping;

[0025] The driving principle of the regulating mechanism includes but is not limited to electricity, magnetism, hydraulic pressure, pneumatic pressure, and related mixed forms.

[0026] The present invention connects different nested components of the combined nozzle blades to fixed components such as a turbine nozzle end wall support plate and movable control components such as an adjustment mechanism, respectively, to achieve the extension and shortening of the nozzle blades under the control of the adjustment structure.

[0027] Compared with conventional radial flow turbines, the nozzle blade telescopic adjustable radial flow turbine adopts retractable nested combined nozzle blades. During operation, different parts of the combined nozzle blades are relatively retracted and pulled under the action of related auxiliary connection transmission adjustment mechanisms, thereby adjusting the throat area of ​​the turbine nozzle blade through the telescopic deformation of the nozzle blade without significantly affecting the nozzle blade outlet airflow angle, thereby improving the turbine's adaptability to operating conditions.

[0028] The above is only a preferred embodiment of the present invention. It should be pointed out that for ordinary technicians in this technical field, several improvements and modifications can be made without departing from the technical principles of the present invention. These improvements and modifications should also be regarded as the scope of protection of the present invention.

Claims

1. A radial flow turbine with adjustable nozzle blades, characterized in that: It includes turbine nozzle blades; the turbine nozzle blades adopt a nested combination structure that can be pulled out and deformed, so as to realize the telescopic deformation of the turbine nozzle blades and adjust the nozzle throat area.

2. A radial flow turbine with adjustable nozzle blade extension according to claim 1, characterized in that: The turbine nozzle vanes are disposed within the turbine case housing.

3. A radial flow turbine with adjustable nozzle blades according to claim 1, characterized in that: The turbine nozzle blade is composed of an embedded trailing edge component 2 and an embedded blade body component 3 which are nested.

4. A radial flow turbine with adjustable nozzle blade extension according to claim 1, characterized in that: After the turbine nozzle blades are retracted, the relative position relationship is a telescopic and adjustable radial flow turbine that wraps around left and right.

5. A radial flow turbine with adjustable nozzle blade extension according to claim 3, characterized in that: Both the embedded trailing edge assembly 2 and the embedded blade body assembly 3 are installed on the nozzle end wall 1 .

6. A radial flow turbine with adjustable nozzle blade extension according to claim 5, characterized in that: The externally embedded blade assembly 3 is fixedly connected to the nozzle end wall 1, and the internally embedded trailing edge assembly 2 is not fixedly connected to the nozzle end wall 1 and the externally embedded blade assembly 3, and can be relatively displaced relative to the fixing part formed by the nozzle end wall 1 and the externally embedded blade assembly 3.

7. A radial flow turbine with adjustable nozzle blade extension according to claim 3, characterized in that: On the connection surface between the nozzle end wall and the embedded trailing edge component 2, a groove and boss structure that fits together and does not affect relative displacement is processed according to actual needs to suppress leakage flow between the nozzle end wall 1 and the embedded trailing edge component 2.

8. A radial flow turbine with adjustable nozzle blade extension according to claim 3, characterized in that: When the supercharger can operate normally at high speed, the embedded trailing edge assembly 2 is completely retracted into the externally embedded blade assembly 3 to ensure that the nozzle throat flow area is sufficient to meet the high-speed operation requirements; when the supercharger intake energy is insufficient, the embedded trailing edge assembly 2 extends outward from the externally embedded blade assembly 3 as needed, thereby reducing the nozzle throat area, increasing the supercharger turbine pressure ratio, and improving the supercharger's working capacity.

9. A radial flow turbine with adjustable nozzle blade extension according to claim 1, characterized in that: The blade is composed of two or more nested components with limit limiting structures. The blade is extended by pulling different nested components through the adjusting mechanism, and the blade is shortened by pushing different nested components through the adjusting mechanism.

10. A radial flow turbine with adjustable nozzle blade extension according to claim 1, characterized in that: The relative position relationship of the opening ends of the nested components of the combined nozzle blades after the blades are fully retracted is completely wrapped inside and outside or partially wrapped inside and outside; the adjustment mechanism is driven by electricity, magnetism, hydraulic pressure, air pressure or a combination of these.

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