CN213064063U - Birotor compressor meridian flow passage suitable for medium and small gas turbines - Google Patents
Birotor compressor meridian flow passage suitable for medium and small gas turbines Download PDFInfo
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- CN213064063U CN213064063U CN202021669889.XU CN202021669889U CN213064063U CN 213064063 U CN213064063 U CN 213064063U CN 202021669889 U CN202021669889 U CN 202021669889U CN 213064063 U CN213064063 U CN 213064063U
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Abstract
A birotor compressor meridian flow channel suitable for a medium and small gas turbine particularly relates to a meridian flow channel formed by a high-pressure compressor and a low-pressure compressor with different rotating speeds. The utility model provides a present problem that pneumatic inefficiency of compressor meridian runner structure. The utility model discloses a low pressure compressor, high pressure compressor and changeover portion, the exit end and the changeover portion of low pressure compressor are connected, and the other end and the entry end of high pressure compressor of changeover portion are connected, and the upper end wall of low pressure compressor and the upper end wall of high pressure compressor constitute upper meridian runner, and the lower end wall of low pressure compressor and the lower end wall of high pressure compressor constitute lower meridian runner. The utility model discloses an adopt the meridian runner that low pressure compressor and the reasonable design of high pressure compressor constitute to select reasonable angle, import and export height ratio, import height and axial length ratio, guaranteed the pneumatic efficiency of compressor under the different rotational speeds of gas turbine compressor.
Description
Technical Field
The utility model relates to a be applicable to middle and small gas turbine birotor compressor meridian runner belongs to the meridian runner that especially relates to the high pressure compressor of different rotational speeds and low pressure compressor constitute.
Background
In the main flow of air and gas of the gas turbine, only the gas turbine consisting of three parts of a gas compressor, a combustion chamber and the gas turbine circulates to form simple circulation, most of the gas turbines adopt a simple circulation scheme, the gas compressor sucks air from the external atmospheric environment and compresses the air step by step to pressurize the air, and meanwhile, the air temperature is correspondingly increased. At present, for a gas turbine unit, an effective method for improving the cycle efficiency of the gas turbine unit is to improve the pneumatic efficiency of a gas compressor, and the improvement of the pneumatic efficiency of the gas compressor not only needs advanced blade design, but also needs a reasonable meridian flow channel structure, and for medium and small gas turbines, almost no meridian flow channel structure of the gas compressor suitable for double rotors with different rotating speeds exists at present.
In summary, a radial flow channel structure suitable for a dual-rotor compressor of a medium-small gas turbine is needed to solve the above problems.
SUMMERY OF THE UTILITY MODEL
The utility model provides a problem that pneumatic inefficiency of present compressor meridian runner structure, the utility model discloses a be applicable to middle and small gas turbine birotor compressor meridian runner. A brief summary of the present invention is provided below in order to provide a basic understanding of some aspects of the present invention. It should be understood that this summary is not an exhaustive overview of the invention. It is not intended to identify key or critical elements of the invention or to delineate the scope of the invention.
The technical scheme of the utility model:
a birotor compressor meridian flow passage suitable for a medium and small gas turbine comprises a low-pressure compressor, a high-pressure compressor and a transition section, wherein the outlet end of the low-pressure compressor is connected with the transition section, the other end of the transition section is connected with the inlet end of the high-pressure compressor, the upper end wall of the low-pressure compressor and the upper end wall of the high-pressure compressor form an upper meridian flow passage, and the lower end wall of the low-pressure compressor and the lower end wall of the high-pressure compressor form a lower meridian flow passage.
Preferably, the low-pressure compressor consists of nine stages of moving and static blades, and the high-pressure compressor consists of nine stages of moving and static blades.
Preferably, the front two stages of the low-pressure compressor adopt an adjustable guide vane design, and the rear seven stages adopt an equal outer diameter design.
Preferably, the high-pressure compressor is designed to have an equal inner diameter.
Preferably, the angle alpha between the last seven stages of the lower end wall of the low-pressure compressor and the axis of the rotor is 6.5-8 degrees.
Preferably, the angle beta between the upper end wall of the high-pressure compressor and the axis of the rotor is 3.9-4.8 degrees.
Preferably, the height of the outlet end of the low-pressure compressor is H2, the height of the inlet end of the low-pressure compressor is H1, and the ratio of the height of the outlet end of the low-pressure compressor H2 to the height of the inlet end of the low-pressure compressor H1 is 0.21-0.22.
Preferably, the height of the outlet end of the high-pressure compressor is H4, the height of the inlet end of the high-pressure compressor is H5, and the ratio of the height of the outlet end of the high-pressure compressor H4 to the height of the inlet end of the high-pressure compressor H5 is 0.41-0.42.
Preferably, the axial length of the low-pressure compressor is H3, and the ratio of the axial length H3 of the low-pressure compressor to the height H1 of the inlet end of the low-pressure compressor is 0.2-0.21.
Preferably, the axial length of the high-pressure compressor is H6, and the ratio of the inlet end height H5 of the high-pressure compressor to the axial length H6 is 0.11-0.12.
The utility model has the advantages that:
1. the meridian flow channel structure formed by the adjustable guide vanes of the front two stages of the inlet end of the low-pressure compressor, the seven stages of the rear equal outer diameter design and the high-pressure compressor equal inner diameter design has high pneumatic efficiency under the condition that the high-pressure compressor and the low-pressure compressor have different rotating speeds.
2. The utility model relates to a meridional runner structure that nine grades of low pressure compressors and nine grades of high pressure compressors constitute through the exit height ratio of chooseing for use reasonable angle, compressor, and the pneumatic efficiency of compressor under the different rotational speeds of gas turbine compressor has been guaranteed to the import height and axial length ratio.
Drawings
FIG. 1 is a schematic diagram of an overall structure of a radial runner of a double-rotor compressor applicable to a medium-small gas turbine.
In the figure, 1-a lower meridian flow passage, 2-an upper meridian flow passage, 3-a low-pressure compressor, 4-a high-pressure compressor and 5-a transition section.
The specific implementation mode is as follows:
in order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be described below with reference to specific embodiments shown in the accompanying drawings. It should be understood that the description is intended to be exemplary, and not to limit the scope of the 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 first embodiment is as follows: the embodiment is described with reference to fig. 1, a birotor compressor radial flow channel suitable for a medium-small gas turbine comprises a low-pressure compressor 3, a high-pressure compressor 4 and a transition section 5, wherein the outlet end of the low-pressure compressor 3 is connected with the transition section 5, the other end of the transition section 5 is connected with the inlet end of the high-pressure compressor 4, the upper end wall of the low-pressure compressor 3 and the upper end wall of the high-pressure compressor 4 form an upper radial flow channel 2, the lower end wall of the low-pressure compressor 3 and the lower end wall of the high-pressure compressor 4 form a lower radial flow channel 1, the transition section 5 adopts a design method for reducing the radial height, the advantage of reducing the radial height by the middle transition section 5 is to reduce centrifugal stress, and the overall;
specifically, the low-pressure compressor 3 is composed of nine stages of moving and static blades, and the high-pressure compressor 4 is composed of nine stages of moving and static blades;
specifically, the front two stages of the low-pressure compressor 3 adopt an adjustable guide vane design, and the rear seven stages adopt an equal outer diameter design;
specifically, the high-pressure compressor 4 is designed to have an equal inner diameter, air enters the low-pressure compressor 3 through an air inlet system, enters the high-pressure compressor 4 through the transition section 5 after being compressed by the low-pressure compressor 3, is further compressed in the high-pressure compressor 4, the high-pressure compressor 4 and the low-pressure compressor 3 are driven by different turbine stages of a gas generator, the pneumatic efficiency of the whole compressor can be realized through the high-pressure and low-pressure compressors with different rotating speeds, and the transition section 5 is designed by a design method for reducing the radial height.
The second embodiment is as follows: the embodiment is described by combining with a figure 1, and the radial flow channel of the double-rotor compressor of the embodiment is suitable for a medium-small gas turbine, wherein an angle alpha between the last seven stages of the lower end wall of the low-pressure compressor 3 and the rotor axis (0) is 6.5-8 degrees;
specifically, an angle beta between the upper end wall of the high-pressure compressor 4 and the rotor axis (0) is 3.9-4.8 degrees, and the pneumatic efficiency of the compressor of the medium-small gas turbine is ensured through a reasonable angle formed by the lower end wall of the low-pressure compressor 3, the upper end wall of the high-pressure compressor 4 and the rotor axis.
The third concrete implementation mode: the embodiment is described by combining fig. 1, and the radial flow channel of the dual-rotor compressor of the embodiment is suitable for a medium-small gas turbine, the outlet end height of the low-pressure compressor 3 is H2, the inlet end height of the low-pressure compressor 3 is H1, and the ratio of the outlet end height H2 to the inlet end height H1 of the low-pressure compressor 3 is 0.21-0.22;
specifically, the axial length of the low-pressure compressor 3 is H3, the ratio of the axial length H3 of the low-pressure compressor 3 to the inlet end height H1 of the low-pressure compressor 3 is 0.2-0.21, and the pneumatic efficiency of the low-pressure compressor 3 is effectively improved by reasonably selecting the ratio of the inlet end height to the outlet end height of the low-pressure compressor 3 and the ratio of the inlet end height to the axial length of the low-pressure compressor 3.
The fourth concrete implementation mode: the embodiment is described with reference to fig. 1, and the radial flow channel of the dual-rotor compressor of the embodiment is suitable for a medium-small gas turbine, the height of the outlet end of the high-pressure compressor 4 is H4, the height of the inlet end of the high-pressure compressor 4 is H5, and the ratio of the height of the outlet end of the high-pressure compressor 4, H4, to the height of the inlet end of the high-pressure compressor 4, H5 is 0.41-0.42;
specifically, the axial length of the high-pressure compressor 4 is H6, the ratio of the inlet end height H5 to the axial length H6 of the high-pressure compressor 4 is 0.11-0.12, and the pneumatic efficiency of the high-pressure compressor 4 is effectively improved by reasonably selecting the ratio of the inlet end height to the outlet end height of the high-pressure compressor 4 and the ratio of the inlet end height to the axial length of the high-pressure compressor 4.
This embodiment is only illustrative of the patent and does not limit the scope of protection thereof, and those skilled in the art can make modifications to its part without departing from the spirit of the patent.
Claims (10)
1. The utility model provides a be applicable to middle and small gas turbine birotor compressor meridian runner which characterized in that: the low-pressure radial flow compressor comprises a low-pressure compressor (3), a high-pressure compressor (4) and a transition section (5), wherein the outlet end of the low-pressure compressor (3) is connected with the transition section (5), the other end of the transition section (5) is connected with the inlet end of the high-pressure compressor (4), the upper end wall of the low-pressure compressor (3) and the upper end wall of the high-pressure compressor (4) form an upper radial flow channel (2), and the lower end wall of the low-pressure compressor (3) and the lower end wall of the high-pressure compressor (4) form a lower radial flow channel (1.
2. The radial runner for the double-rotor compressor of the medium-small gas turbine as claimed in claim 1, is characterized in that: the low-pressure compressor (3) consists of nine stages of movable and stationary blades, and the high-pressure compressor (4) consists of nine stages of movable and stationary blades.
3. The radial runner for the double-rotor compressor of the medium-small gas turbine as claimed in claim 2, wherein: the front two stages of the low-pressure compressor (3) are designed by adjustable guide vanes, and the rear seven stages are designed by equal outer diameters.
4. The radial runner for the double-rotor compressor of the medium-small gas turbine as claimed in claim 2, wherein: the high-pressure compressor (4) is designed to have an equal inner diameter.
5. The radial runner for the double-rotor compressor of the medium-small gas turbine as claimed in claim 3, wherein: the angle alpha between the rear seven stages of the lower end wall of the low-pressure compressor (3) and the axis (0) of the rotor is 6.5-8 degrees.
6. The radial runner for the double-rotor compressor of the medium-small gas turbine as claimed in claim 4, wherein: the upper end wall of the high-pressure compressor (4) forms an angle beta of 3.9-4.8 degrees with the rotor axis (0).
7. The radial runner for the double-rotor compressor of the medium-small gas turbine as claimed in claim 1, is characterized in that: the height of the outlet end of the low-pressure compressor (3) is H2, the height of the inlet end of the low-pressure compressor (3) is H1, and the ratio of the height H2 of the outlet end of the low-pressure compressor (3) to the height H1 of the inlet end is 0.21-0.22.
8. The radial runner for the double-rotor compressor of the medium-small gas turbine as claimed in claim 1, is characterized in that: the height of the outlet end of the high-pressure compressor (4) is H4, the height of the inlet end of the high-pressure compressor (4) is H5, and the ratio of the height of the outlet end H4 to the height of the inlet end H5 of the high-pressure compressor (4) is 0.41-0.42.
9. The radial runner for the double-rotor compressor of the medium-small gas turbine as claimed in claim 7, is characterized in that: the axial length of the low-pressure compressor (3) is H3, and the ratio of the axial length H3 of the low-pressure compressor (3) to the height H1 of the inlet end of the low-pressure compressor (3) is 0.2-0.21.
10. The radial runner for the double-rotor compressor of the medium-small gas turbine as claimed in claim 8, wherein: the axial length of the high-pressure compressor (4) is H6, and the ratio of the inlet end height H5 of the high-pressure compressor (4) to the axial length H6 is 0.11-0.12.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202021669889.XU CN213064063U (en) | 2020-08-12 | 2020-08-12 | Birotor compressor meridian flow passage suitable for medium and small gas turbines |
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| CN202021669889.XU CN213064063U (en) | 2020-08-12 | 2020-08-12 | Birotor compressor meridian flow passage suitable for medium and small gas turbines |
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| CN213064063U true CN213064063U (en) | 2021-04-27 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115163559A (en) * | 2022-06-24 | 2022-10-11 | 中国船舶重工集团公司第七0三研究所 | Low-loss gas compressor transition section structure |
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- 2020-08-12 CN CN202021669889.XU patent/CN213064063U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115163559A (en) * | 2022-06-24 | 2022-10-11 | 中国船舶重工集团公司第七0三研究所 | Low-loss gas compressor transition section structure |
| CN115163559B (en) * | 2022-06-24 | 2024-05-17 | 中国船舶重工集团公司第七0三研究所 | Low-loss transition section structure of gas compressor |
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