CN215908115U - Meridian flow channel structure suitable for low-pressure compressor of 10MW grade gas turbine - Google Patents
Meridian flow channel structure suitable for low-pressure compressor of 10MW grade gas turbine Download PDFInfo
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- CN215908115U CN215908115U CN202122136742.5U CN202122136742U CN215908115U CN 215908115 U CN215908115 U CN 215908115U CN 202122136742 U CN202122136742 U CN 202122136742U CN 215908115 U CN215908115 U CN 215908115U
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Abstract
A meridian flow channel structure applicable to a low-pressure compressor of a 10MW grade gas turbine belongs to the technical field of gas turbines. The utility model comprises an upper meridian flow channel structure and a lower meridian flow channel structure which are composed of an upper end wall and a lower end wall of four-stage moving and static blades; the four-stage movable and static blades comprise first-stage static blades, first-stage moving blades, second-stage static blades, second-stage moving blades, third-stage static blades, third-stage moving blades, fourth-stage static blades and fourth-stage moving blades. The utility model provides a meridian flow channel structure of a four-stage movable vane, which is designed to have extremely high pneumatic efficiency, and simultaneously, in order to ensure an outlet airflow angle, an outlet of the fourth-stage movable vane is adjusted by adopting two stages of stationary vanes.
Description
Technical Field
The utility model relates to a radial flow channel of a low-pressure compressor of a medium-sized and small-sized combustion engine in aeronautical modification, belonging to the technical field of gas turbines.
Background
The radial flow channels of the gas turbine are the channels through which the gas flows in and out. In the prior art, for a generating unit of a medium-small gas turbine, a double-rotor form formed by combining a high-pressure compressor and a low-pressure compressor is mostly adopted, and an effective method for improving the cycle efficiency of the generating unit is to improve the efficiency of the compressor, and the improvement of the efficiency of the compressor not only needs advanced blade design but also needs a reasonable meridian flow channel structure. For a 10MW grade gas turbine unit, almost no patent is provided for a meridian flow passage structure of a low-pressure compressor at present.
Therefore, a new radial flow channel structure suitable for a low-pressure compressor of a 10MW grade gas turbine needs to be provided to solve the above technical problems.
SUMMERY OF THE UTILITY MODEL
The utility model has been developed in order to solve the problem of providing a radial flow channel structure suitable for a low-pressure compressor of a 10MW grade gas turbine, and solving the problem of aerodynamic efficiency of the low-pressure compressor of a 10MW grade gas turbine set, and a brief summary of the utility model is given below in order to provide a basic understanding of some aspects of the utility model. It should be understood that this summary is not an exhaustive overview of the utility model. It is not intended to determine the key or critical elements of the present invention, nor is it intended to limit the scope of the present invention.
The technical scheme of the utility model is as follows:
a meridian flow channel structure suitable for a low-pressure compressor of a 10MW grade gas turbine comprises an upper meridian flow channel structure and a lower meridian flow channel structure, wherein the upper meridian flow channel structure and the lower meridian flow channel structure are formed by upper end walls and lower end walls of four-grade moving and static blades;
the four-stage movable and static blades comprise first-stage static blades, first-stage moving blades, second-stage static blades, second-stage moving blades, third-stage static blades, third-stage moving blades, fourth-stage static blades and fourth-stage moving blades.
Preferably: the angle alpha 1 formed by the lower end wall of the first stage stationary blade and the axis is 18-20 degrees, and the angle alpha 2 formed by the lower end wall of the first stage moving blade and the axis is 21-23 degrees.
Preferably: the angle alpha 3 formed by the lower end wall of the second stage stationary blade and the axis is 19-21 degrees, and the angle alpha 4 formed by the lower end wall of the second stage moving blade and the axis is 15-17 degrees.
Preferably: the angle α 5 formed by the lower endwall of the third stage stationary blade and the axis is 5 to 7 °, and the angle α 6 formed by the lower endwall of the third stage moving blade and the axis is 4 to 6 °.
Preferably: the angle alpha 7 formed by the lower end wall of the fourth stage stationary blade and the axis is 2-3 degrees, and the angle alpha 8 formed by the lower end wall of the fourth stage moving blade and the axis is 4-6 degrees.
Preferably: the first stage vane upper endwall is in parallel relationship with the axis.
Preferably: an angle beta 1 between the upper end wall of the first-stage movable blade and the axis is 15-17 degrees, and an angle beta 2 between the upper end wall of the second-stage stationary blade, the upper end wall of the second-stage movable blade, the upper end wall of the third-stage stationary blade, the upper end wall of the third-stage movable blade, the upper end wall of the fourth-stage stationary blade and the upper end wall of the fourth-stage movable blade and the axis is 8-9 degrees.
Preferably: and a first-stage adjusting blade and a second-stage adjusting blade are arranged at the outlet of the fourth-stage moving blade.
Preferably: the ratio of the inlet height L1 to the outlet height L2 is between 0.38 and 0.41.
Preferably: the ratio of the inlet height L1 to the axial length L3 is between 0.61 and 0.67.
The utility model has the following beneficial effects:
1. the meridian flow channel structure of the low-pressure compressor of the 10MW grade gas turbine is suitable for realizing the meridian flow channel structure of the low-pressure compressor of the 10MW grade gas turbine, and is different from the design of a 20-50 grade gas turbine, the low-pressure compressor of the 10MW grade gas turbine adopts a 4-grade moving blade design scheme, the meridian flow channel structure of a four-grade moving blade is provided by the design, meanwhile, the design has extremely high pneumatic efficiency, and meanwhile, in order to ensure an outlet airflow angle, the outlet of a fourth-grade moving blade is adjusted by adopting two-grade moving blades;
2. the meridian flow channel structure of the low-pressure compressor of the 10MW grade gas turbine selects four stages in the low-pressure compressor stage number, the upper meridian flow channel and the lower meridian flow channel form a certain reasonable angle with the center line, and the outlet of the final stage movable blade adopts two stages of guide vanes to adjust the airflow direction, so that the pneumatic efficiency of the four-stage low-pressure compressor at 7850 revolutions per minute is ensured;
3. the meridian flow channel structure of the low-pressure compressor of the gas turbine with the 10MW grade, disclosed by the utility model, is simple in structure, ingenious in design and suitable for popularization and application.
Drawings
FIG. 1 is a schematic structural diagram of a meridian flow channel structure of a low-pressure compressor of a gas turbine with a 10MW grade;
FIG. 2 is a schematic structural view of a first stage stationary blade of the present invention;
in the figure, 1-lower radial flow path structure, 2-upper radial flow path structure, 3-first stage stationary blades, 4-first stage moving blades, 5-second stage stationary blades, 6-second stage moving blades, 7-third stage stationary blades, 8-third stage moving blades, 9-fourth stage stationary blades, 10-fourth stage moving blades, 11-first stage adjusting blades, and 12-second stage adjusting blades.
Detailed Description
In order that the objects, aspects and advantages of the utility model will become more apparent, the utility model will be described by way of example only, and in connection with the accompanying drawings. It is to be understood that such description is merely illustrative and not intended to limit the scope of the present invention. Moreover, in the following description, descriptions of well-known structures and techniques are omitted so as to not unnecessarily obscure the concepts of the present invention.
The connection mentioned in the utility model is divided into fixed connection and detachable connection, the fixed connection is non-detachable connection and includes but is not limited to folding edge connection, rivet connection, bonding connection, welding connection and other conventional fixed connection modes, the detachable connection includes but is not limited to threaded connection, snap connection, pin connection, hinge connection and other conventional detachment modes, when the specific connection mode is not clearly limited, at least one connection mode can be found in the existing connection modes by default to realize the function, and the skilled person can select according to the needs. For example: the fixed connection selects welding connection, and the detachable connection selects hinge connection.
The first embodiment is as follows: the embodiment is described with reference to fig. 1-2, and the radial flow channel structure of the low-pressure compressor of the gas turbine with 10MW grade of the embodiment comprises an upper radial flow channel structure 2 and a lower radial flow channel structure 1 which are composed of upper and lower end walls of four-stage moving and static blades, wherein a radial flow channel is formed in a similar equal-intermediate-diameter mode, and the upper and lower end walls of the blades and a central line form a certain angle;
the four-stage movable and static blades comprise first-stage static blades 3, first-stage moving blades 4, second-stage static blades 5, second-stage moving blades 6, third-stage static blades 7, third-stage moving blades 8, fourth-stage static blades 9 and fourth-stage moving blades 10, four-stage movable and static blades are selected on the low-pressure compressor stage, and the upper meridian flow channel structure 2 and the lower meridian flow channel structure 1 form a certain reasonable angle with a central line.
The angle α 1 formed by the lower endwall of first stage stationary blade 3 and axis 0 is 18 to 20 °, and the angle α 2 formed by the lower endwall of first stage moving blade 4 and axis 0 is 21 to 23 °.
The angle α 3 formed by the lower endwall of second stage stationary vanes 5 and the axis 0 is 19 to 21 °, and the angle α 4 formed by the lower endwall of second stage moving vanes 6 and the axis 0 is 15 to 17 °.
The angle α 5 formed by the lower endwall of third stage stationary blade 7 and axis 0 is 5 to 7 °, and the angle α 6 formed by the lower endwall of third stage moving blade 8 and axis 0 is 4 to 6 °.
The angle α 7 formed by the lower endwall of the fourth stage stationary blade 9 and the axis 0 is 2 to 3 °, and the angle α 8 formed by the lower endwall of the fourth stage moving blade 10 and the axis 0 is 4 to 6 °.
The upper endwalls of the first stage vanes 3 are in parallel relationship with the axis 0.
An angle beta 1 between the upper end wall of the first-stage moving blade 4 and the axis 0 is 15-17 degrees, and an angle beta 2 between the upper end walls of the second-stage stationary blades 5, the second-stage moving blades 6, the third-stage stationary blades 7, the third-stage moving blades 8, the fourth-stage stationary blades 9 and the fourth-stage moving blades 10 and the axis 0 is 8-9 degrees.
The outlet of the fourth stage moving blade 10 is provided with a first stage adjusting blade 11 and a second stage adjusting blade 12, and the outlet of the last stage moving blade adopts two stages of guide vanes to adjust the airflow direction, so that the pneumatic efficiency of a four-stage low-pressure compressor at 7850 revolutions per minute is ensured.
The ratio of the inlet height L1 to the outlet height L2 is between 0.38 and 0.41.
The ratio of the inlet height L1 to the axial length L3 is between 0.61 and 0.67.
It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of example embodiments according to the present application. As used herein, the singular forms "a", "an" and "the" are intended to include the plural forms as well, and it should be understood that when the terms "comprises" and/or "comprising" are used in this specification, they specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof, unless the context clearly indicates otherwise.
The relative arrangement of the components and steps, the numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present invention unless specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective portions shown in the drawings are not drawn in an actual proportional relationship for the convenience of description. Techniques, methods, and apparatus known to those of ordinary skill in the relevant art may not be discussed in detail but are intended to be part of the specification where appropriate. In all examples shown and discussed herein, any particular value should be construed as merely illustrative, and not limiting. Thus, other examples of the exemplary embodiments may have different values. 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, further discussion thereof is not required in subsequent figures.
In the description of the present invention, it is to be understood that the orientation or positional relationship indicated by the orientation words such as "front, rear, upper, lower, left, right", "lateral, vertical, horizontal" and "top, bottom", etc. are usually based on the orientation or positional relationship shown in the drawings, and are only for convenience of description and simplicity of description, and in the case of not making a reverse description, these orientation words do not indicate and imply that the device or element being referred to must have a specific orientation or be constructed and operated in a specific orientation, and therefore, should not be considered as limiting the scope of the present invention; the terms "inner and outer" refer to the inner and outer relative to the profile of the respective component itself.
Spatially relative terms, such as "above … …," "above … …," "above … …," "above," and the like, may be used herein for ease of description to describe one device or feature's spatial relationship to another device or feature as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations of the device in use or operation in addition to the orientation depicted in the figures. For example, if a device in the figures is turned over, devices described as "above" or "on" other devices or configurations would then be oriented "below" or "under" the other devices or configurations. Thus, the exemplary term "above … …" can include both an orientation of "above … …" and "below … …". The device may be otherwise variously oriented (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.
It should be noted that the terms "first," "second," and the like in the description and claims of this application and in the drawings described above are used for distinguishing between similar elements and not necessarily for describing a particular sequential or chronological order. It is to be understood that the data so used is interchangeable under appropriate circumstances such that the embodiments of the application described herein are capable of operation in sequences other than those illustrated or described herein.
It should be noted that, in the above embodiments, as long as the technical solutions can be aligned and combined without contradiction, those skilled in the art can exhaust all possibilities according to the mathematical knowledge of the alignment and combination, and therefore, the present invention does not describe the technical solutions after alignment and combination one by one, but it should be understood that the technical solutions after alignment and combination have been disclosed by the present invention.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (7)
1. The utility model provides a be applicable to 10MW grade gas turbine low pressure compressor meridian runner structure which characterized in that: comprises an upper meridian flow channel structure (2) and a lower meridian flow channel structure (1) which are composed of an upper end wall and a lower end wall of four stages of moving and static blades;
the four-stage moving static vanes comprise first-stage static vanes (3), first-stage moving blades (4), second-stage static vanes (5), second-stage moving blades (6), third-stage static vanes (7), third-stage moving blades (8), fourth-stage static vanes (9) and fourth-stage moving blades (10);
the angle alpha 1 formed by the lower end wall of the first stage stationary blade (3) and the axis (0) is 18-20 degrees, and the angle alpha 2 formed by the lower end wall of the first stage moving blade (4) and the axis (0) is 21-23 degrees.
2. The radial flow channel structure of the low-pressure compressor of the 10 MW-grade gas turbine as claimed in claim 1, wherein: the angle alpha 3 formed by the lower end wall of the second stage stationary blade (5) and the axis (0) is 19-21 degrees, and the angle alpha 4 formed by the lower end wall of the second stage moving blade (6) and the axis (0) is 15-17 degrees.
3. The radial flow channel structure of the low-pressure compressor of the 10MW grade gas turbine as claimed in claim 2, wherein: the angle alpha 5 formed by the lower end wall of the third stage stationary blade (7) and the axis (0) is 5-7 degrees, and the angle alpha 6 formed by the lower end wall of the third stage moving blade (8) and the axis (0) is 4-6 degrees.
4. The radial flow channel structure of the low-pressure compressor of the 10MW grade gas turbine as claimed in claim 3, wherein: the angle alpha 7 formed by the lower end wall of the fourth stage stationary blade (9) and the axis (0) is 2-3 degrees, and the angle alpha 8 formed by the lower end wall of the fourth stage moving blade (10) and the axis (0) is 4-6 degrees.
5. The radial flow channel structure of the low-pressure compressor of the 10MW grade gas turbine as claimed in claim 4, wherein: the upper endwall of the first stage stator vanes (3) is in parallel relationship with the axis (0).
6. The radial flow channel structure of the low-pressure compressor of the 10MW grade gas turbine as claimed in claim 5, wherein: the angle beta 1 between the upper end wall of the first-stage moving blade (4) and the axis (0) is 15-17 degrees, and the angle beta 2 between the upper end walls of the second-stage stationary blade (5), the second-stage moving blade (6), the third-stage stationary blade (7), the third-stage moving blade (8), the fourth-stage stationary blade (9) and the fourth-stage moving blade (10) and the axis (0) is 8-9 degrees.
7. The radial flow channel structure of the low-pressure compressor of the 10MW grade gas turbine as claimed in claim 6, wherein: and a first-stage adjusting blade (11) and a second-stage adjusting blade (12) are arranged at the outlet of the fourth-stage moving blade (10).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122136742.5U CN215908115U (en) | 2021-09-06 | 2021-09-06 | Meridian flow channel structure suitable for low-pressure compressor of 10MW grade gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122136742.5U CN215908115U (en) | 2021-09-06 | 2021-09-06 | Meridian flow channel structure suitable for low-pressure compressor of 10MW grade gas turbine |
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| Publication Number | Publication Date |
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| CN215908115U true CN215908115U (en) | 2022-02-25 |
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| CN202122136742.5U Active CN215908115U (en) | 2021-09-06 | 2021-09-06 | Meridian flow channel structure suitable for low-pressure compressor of 10MW grade gas turbine |
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- 2021-09-06 CN CN202122136742.5U patent/CN215908115U/en active Active
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