CN114810223A

CN114810223A - Guide vane structure adaptive to mixed flow turbine

Info

Publication number: CN114810223A
Application number: CN202210640572.0A
Authority: CN
Inventors: 吴贺松; 吴张武
Original assignee: Chengdu Xiling New Kinetic Energy Technology Co ltd
Current assignee: Chengdu Xiling New Kinetic Energy Technology Co ltd
Priority date: 2022-06-07
Filing date: 2022-06-07
Publication date: 2022-07-29

Abstract

The invention discloses a guide vane structure adaptive to a mixed flow turbine, which comprises a guide vane ring and a plurality of vanes, wherein the vanes are arranged on the guide vane ring, the vanes are distributed in an annular array around the axial lead of the guide vane ring, an air inlet gap is arranged between every two adjacent vanes, the vanes are arranged in an inclined manner, the inclined direction of the vanes is the direction opposite to the center of the guide vane ring, and when the vanes are closest to the profile of the air inlet side of the mixed flow turbine, the vanes are parallel to the profile of the air inlet side of the mixed flow turbine. In the application, the blades are obliquely arranged, so that the air inflow of the air flow entering the mixed flow turbine is ensured to be consistent with that of the air flow without guide vanes; compared with the guide vane matched with the conventional radial turbine, when the airflow sequentially flows through the guide vane and the mixed flow turbine inlet edge, the gas has no large steering angle, the energy loss is less, and the efficiency of the turbine can be improved.

Description

Guide vane structure adaptive to mixed flow turbine

Technical Field

The invention relates to the technical field of turbochargers, in particular to a guide vane structure adaptive to a mixed flow turbine.

Background

The turbocharger is an important part of high-end automobile engines, and has the main functions of increasing the air intake density of the automobile engine, enabling the fuel of the automobile engine to be more fully combusted and increasing the driving force of the engine. Common functional components of turbochargers include: a turbine, a compressor and an intermediate body. The intermediate body functions to connect the turbine and the compressor and provides rotational support for the turbine and the compressor. The turbine drives the turbine to rotate by using high-temperature gas exhausted by the engine, the pressure impeller of the air compressor is driven to rotate through the support of the intermediate body, the air density is improved through the air compressor, so that more gas enters the engine, and the power of the engine is further improved.

The engine has different air displacement and air inflow under high-speed and low-speed working conditions, and in order to adjust air inflow and exhaust under different working conditions, a common adjusting mechanism is divided into an exhaust gas bypass structure and a variable cross-section structure.

As shown in fig. 1, a guide vane 04 is arranged between the intermediate body 01 and the volute 02 at the air inlet edge of the turbine 03, and the flow area of the air flow is controlled by controlling the opening angle of the guide vane, so that the adjustment of the air intake amount under different working conditions is realized.

As shown in fig. 2 and 3, the conventional guide vane 04 includes a guide vane ring 41 and a blade 42, the blade is vertically mounted on the guide vane ring, and this structure has a large effect on the radial-flow turbine, but when the guide vane is adapted to the francis turbine, since the leading edge profile 31 of the francis turbine is not parallel to the axial direction of the turbine, after the airflow passes through the guide vane, the airflow along the axial direction is different from the leading edge trend of the francis turbine, so this guide vane structure cannot adapt to the function of the francis turbine, and the function of the francis turbine is limited.

Therefore, it is necessary to develop a guide vane structure adapted to the mixed flow turbine to solve the above problems.

Disclosure of Invention

The invention aims to solve the problems and designs a guide vane structure adaptive to a mixed flow turbine.

The invention realizes the purpose through the following technical scheme:

the utility model provides a stator structure of adaptation mixed flow turbine, includes guide vane ring, a plurality of blades, and a plurality of blades are installed on the guide vane ring, and a plurality of blades are annular array around the axial lead of guide vane ring and distribute, are provided with air intake gap between two adjacent blades, and the blade slope sets up, and the incline direction of blade is the opposite direction in the center towards the guide vane ring, and when the blade was nearest apart from the leading edge profile of mixed flow turbine, the blade was parallel with the leading edge profile of mixed flow turbine.

The invention has the beneficial effects that:

in the application, the blades are obliquely arranged, so that the air inflow of the air flow entering the mixed flow turbine is ensured to be consistent with that of the air flow without guide vanes; compared with the guide vane matched with the conventional radial turbine, when the airflow sequentially flows through the guide vane and the mixed flow turbine inlet edge, the gas has no large steering angle, the energy loss is less, and the efficiency of the turbine can be improved.

Drawings

FIG. 1 is a schematic view of a prior art vane assembly;

FIG. 2 is a schematic view of a prior art vane configuration; in the figure, A is a front view and B is a side sectional view;

FIG. 3 is a schematic inlet path of a prior art vane configuration;

FIG. 4 is a vane assembly schematic view of an embodiment of the present application;

FIG. 5 is a schematic view of a vane structure in an embodiment of the present application; in the figure, A is a front view and B is a side sectional view;

FIG. 6 is a schematic inlet route of a guide vane structure in the embodiment of the present application;

FIG. 7 is a graphical representation of the total static expansion ratio versus total static efficiency of the present application versus a prior art product;

in the figure: 01. an intermediate; 02. a volute; 03. a turbine; 31. an air inlet edge profile; 04. a guide vane; 41. a guide vane ring; 42. a blade.

Detailed Description

In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention. It is to be understood that the embodiments described are only a few embodiments of the present invention, and not all embodiments. The components of embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.

Thus, the following detailed description of the embodiments of the present invention, presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.

In the description of the present invention, it is to be understood that the terms "upper", "lower", "inside", "outside", "left", "right", and the like, indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, or the orientations or positional relationships that the products of the present invention are conventionally placed in use, or the orientations or positional relationships that are conventionally understood by those skilled in the art, and are used for convenience of describing the present invention and simplifying the description, but do not indicate or imply that the devices or elements referred to must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention.

Furthermore, the terms "first," "second," and the like are used merely to distinguish one description from another, and are not to be construed as indicating or implying relative importance.

In the description of the present invention, it is also to be noted that, unless otherwise explicitly stated or limited, the terms "disposed" and "connected" are to be interpreted broadly, and for example, "connected" may be a fixed connection, a detachable connection, or an integral connection; can be mechanically or electrically connected; the connection may be direct or indirect via an intermediate medium, and may be a communication between the two elements. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.

The following detailed description of embodiments of the invention refers to the accompanying drawings.

As shown in fig. 4 to 5, a guide vane structure adapted to a francis turbine includes a guide vane ring 41 and a plurality of blades 42, the plurality of blades 42 are mounted on the guide vane ring 41, the plurality of blades 42 are distributed in an annular array around an axial line of the guide vane ring 41, an intake gap is provided between two adjacent blades 42, the blades 42 are arranged in an inclined manner, an inclined direction of the blades 42 is an opposite direction toward a center of the guide vane ring 41, and when the blades 42 are closest to a leading edge profile 31 of the francis turbine 03, the blades 42 are parallel to the leading edge profile 31 of the francis turbine 03. In the air inlet gap, the cross section of any one of the mutually corresponding positions of the two blades 42 is a parallelogram, and the oblique sides of the cross section of the parallelogram are parallel to the air inlet side profile 31 of the mixed flow turbine 03;

as shown in fig. 5, each of the plurality of blades 42 is formed in a plate-like structure with both tips and a middle portion thereof protruding to both sides, and is mounted on the vane ring 41 in an attitude: the center of the guide vane ring 41 forms a certain angle with the connecting line of the two ends of the vanes 42, and the degree of the specific angle is determined according to the number of the vanes 42, which is the prior art and is not described herein.

As shown in fig. 6, the shape of the conventional blade 42 is changed by the present application, so that the airflow entering between two adjacent blades 42 is confined in the intake gap, and the cross-sectional shape of the intake gap is adapted, and finally the output airflow from between two blades 42 acts on the mixed flow turbine 03 in the cross-sectional shape, and because the output airflow matches with the intake edge profile 31 of the mixed flow turbine 03, all the output airflow acts on the mixed flow turbine 03, and the gas has no large turning angle, so that the energy loss is less, and the turbine efficiency is improved; the structure can be designed to be more compact under the condition of the same flow.

As shown in fig. 7, the efficiency of the improved turbine is significantly improved.

The foregoing is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, various modifications and decorations can be made without departing from the technical principle of the present invention, and these modifications and decorations should also be regarded as the protection scope of the present invention.

Claims

1. The utility model provides a stator structure of adaptation mixed flow turbine, includes guide vane ring, a plurality of blades, and a plurality of blades are installed on the guide vane ring, and a plurality of blades are annular array around the axial lead of guide vane ring and distribute, are provided with air intake gap between two adjacent blades, and its characterized in that, blade slope sets up, and the incline direction of blade is the opposite direction of the center towards the guide vane ring, and when the blade was nearest apart from the leading edge profile of mixed flow turbine, the blade was parallel with the leading edge profile of mixed flow turbine.