CN111911288B - Gas turbine starting structure - Google Patents
Gas turbine starting structure Download PDFInfo
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- CN111911288B CN111911288B CN202010850918.0A CN202010850918A CN111911288B CN 111911288 B CN111911288 B CN 111911288B CN 202010850918 A CN202010850918 A CN 202010850918A CN 111911288 B CN111911288 B CN 111911288B
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- compressor
- gas turbine
- compressor casing
- casing
- starting structure
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/26—Starting; Ignition
- F02C7/268—Starting drives for the rotor, acting directly on the rotor of the gas turbine to be started
- F02C7/27—Fluid drives
Abstract
An embodiment of the present invention provides a gas turbine starting structure, including: the compressor comprises a compressor casing (1), wherein a compressor impeller (5) is arranged on the inner side of the compressor casing (1), and the compressor impeller (5) rotates around a rotating shaft (R) positioned in the center of the inner side of the compressor casing (1); the bleed air channel casing (2) is positioned outside the compressor casing (1) and is axially matched with the compressor casing (1) so as to form an annular bleed air channel (3) with the compressor casing (1); the air compressor casing (1) is circumferentially provided with an air guiding seam (4). The structure has the advantages of simple structure and portability on the one hand. On the other hand, the problem that the starting device of the gas turbine in the prior art cannot be reused is also solved.
Description
Technical Field
The invention relates to the technical field of gas turbines, in particular to a gas turbine starting structure.
Background
The gas turbine is an internal combustion power machine which drives an impeller to rotate at a high speed by continuous airflow to do work and convert chemical energy of fuel into mechanical energy.
The gas turbine generally comprises three parts, namely a compressor, a combustion chamber and a turbine. When the gas turbine normally works, the gas compressor sucks in outside air and compresses the air, high-pressure air enters the combustion chamber to be mixed with atomized fuel and then is combusted to generate high-temperature and high-pressure gas, the gas impacts the turbine to do work, external load rotors such as the gas compressor and the turbine are driven to rotate at a high speed, and the energy of the fuel is continuously converted into mechanical energy.
The amount of work consumed by the compressor to compress the air needs to be provided by the turbine. During the period of time during which the power generated by the turbine before and after ignition during the startup of the gas turbine is less than the power required by the compressor, the gas turbine requires additional power to drive its rotor system. Thus, the gas turbine requires the assistance of an external power plant for starting.
At present, the starting modes of the gas turbine mainly comprise motor driving, blowing starting and explosion starting. The former two ways inevitably have additional starting devices attached to the outside of the gas turbine unit, occupying the whole space and increasing the weight of the unit. Explosion starting can cause certain hidden trouble to the overall safe operation of the gas turbine. And the starting device is only used as a starting device and is independent from the gas turbine set, and the normal operation of the gas turbine after starting is not substantially facilitated.
Therefore, how to provide a structure which can at least partially solve the defects in the prior art is of great significance.
Disclosure of Invention
In view of the defects in the prior art, an embodiment of the present invention provides a gas turbine starting structure, including:
the inner side of the compressor casing 1 is provided with a compressor impeller 5, and the compressor impeller 5 rotates around a rotating shaft R positioned in the center of the inner side of the compressor casing 1;
the bleed air channel casing 2 is positioned outside the compressor casing 1 and is axially matched with the compressor casing 1 so as to form an annular air flow channel 3 with the compressor casing 1;
wherein, an air guiding seam 4 is arranged on the compressor casing 1 in the circumferential direction.
In one embodiment, the total cross-sectional area of the gas introduction slits 4 is smaller than the cross-sectional area of the annular gas flow channel 3.
In one embodiment, the number of the air induction slots 4 is multiple, and the air induction slots are arranged at equal intervals along the circumferential direction of the compressor casing 1.
In one embodiment, the number of the air-guiding slits 4 is x Nm, where N is a preset density factor, and m is the number of blades of the compressor wheel 5.
In one embodiment, the air induction slit 4 comprises an inner opening 41 and an outer opening 42;
the inner opening 41 faces the inside of the compressor casing 1, and the outer opening 42 faces the annular airflow passage 3.
In one embodiment, the height D of the air introduction slit 4fComprises the following steps:
wherein D isiThe diameter of an air inlet of a compressor casing; l is the axial width of the air introduction slit 4 along the rotation axis R; n is a radical of1A preset flow velocity coefficient is obtained; n is a radical of2Is a preset flow coefficient.
In one embodiment, the inner opening 41 forms an angle θ with a tangent of an inner wall surface of the compressor casing 1iComprises the following steps:
wherein D ismThe minimum interlobe gap between the compressor casing 1 and the compressor wheel 5.
In one embodiment, the outer opening 42 forms an angle θ with the tangent of the outer wall of the compressor casing 1oComprises the following steps:
in one embodiment, the compressor casing 1 is provided with a mating surface 11 protruding outwards to axially mate with the bleed air channel casing 2.
In one embodiment, the compressor casing 1 and the bleed air channel casing 2 are fixed by a flange 12.
When the gas turbine is started, high-speed high-pressure airflow is blown into an annular airflow channel 3 in the gas turbine starting structure provided by the embodiment of the invention by an external fan, the high-speed high-pressure airflow enters the inner side of a compressor casing 1 through an air guide seam 4 to form high-speed jet flow, and the high-speed jet flow impacts a compressor impeller 5 positioned on the inner side of the compressor casing 1 so as to enable the compressor impeller 5 to start rotating around a rotating shaft R, thereby realizing the air blowing starting of the gas turbine.
When the gas turbine works under variable working conditions, the annular airflow channel 3 in the gas turbine starting structure provided by the embodiment of the invention is extracted by the external fan, so that negative pressure is formed inside the annular airflow channel 3, and the air inside the compressor casing 1 is extracted to the annular airflow channel 3 through the air introducing seam 4, thereby achieving the purpose of stabilizing the working state of the compressor and enhancing the stability of the variable working conditions of the gas turbine.
Therefore, the gas turbine starting structure provided by the embodiment of the invention only needs to additionally arrange the bleed air channel casing 2 without excessively increasing the weight of the unit, and has the advantages of simple structure and portability. On the other hand, after the gas turbine is started, the structure still can play a role in enhancing the stability of the variable working condition of the gas turbine, so that the problem that the starting device of the gas turbine in the prior art cannot be reused is solved.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and those skilled in the art can also obtain other drawings according to the drawings without creative efforts.
FIG. 1 is a schematic diagram of a gas turbine startup configuration according to an embodiment of the invention;
FIG. 2 is an axial cross-sectional view of a gas turbine startup configuration according to an embodiment of the invention;
FIG. 3 is an enlarged view of portion I of FIG. 1;
FIG. 4 is an enlarged view of section II of FIG. 2;
FIG. 5 is a schematic diagram illustrating the operation of a gas turbine during startup of a gas turbine according to an embodiment of the present invention;
fig. 6 is a schematic diagram of an operation principle of the gas turbine startup structure according to the embodiment of the invention when the gas turbine is expanded and stabilized.
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, and it is obvious that the described embodiments are some, but not all, embodiments of the present 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.
In the description of the embodiments of the present invention, it should be noted that the terms "center", "longitudinal", "lateral", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the embodiments of the present invention and simplifying the description, but do not indicate or imply that the referred devices or elements must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the embodiments of the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the embodiments of the present invention, it should be noted that, unless explicitly stated or limited otherwise, the terms "connected" and "connected" are to be interpreted broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; may be directly connected or indirectly connected through an intermediate. Specific meanings of the above terms in the embodiments of the present invention can be understood in specific cases by those of ordinary skill in the art.
In embodiments of the invention, unless expressly stated or limited otherwise, the first feature "on" or "under" the second feature may be directly contacting the first and second features or indirectly contacting the first and second features through intervening media. Also, a first feature "on," "over," and "above" a second feature may be directly or diagonally above the second feature, or may simply indicate that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature may be directly under or obliquely under the first feature, or may simply mean that the first feature is at a lesser elevation than the second feature.
In the description herein, references to the description of the term "one embodiment," "some embodiments," "an example," "a specific example," or "some examples," etc., mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of an embodiment of the invention. In this specification, the schematic representations of the terms used above are not necessarily intended to refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, various embodiments or examples and features of different embodiments or examples described in this specification can be combined and combined by one skilled in the art without contradiction.
Fig. 1 is a schematic diagram of a gas turbine starting structure provided in an embodiment of the present invention, and referring to fig. 1, the structure includes:
the inner side of the compressor casing 1 is provided with a compressor impeller 5, and the compressor impeller 5 rotates around a rotating shaft R positioned in the center of the inner side of the compressor casing 1;
the bleed air channel casing 2 is positioned outside the compressor casing 1 and is axially matched with the compressor casing 1 so as to form an annular air flow channel 3 with the compressor casing 1;
wherein, the compressor casing 1 is circumferentially provided with an air guiding seam 4.
When the gas turbine is started, high-speed high-pressure airflow is blown into an annular airflow channel 3 in the gas turbine starting structure provided by the embodiment of the invention by an external fan, the high-speed high-pressure airflow enters the inner side of a compressor casing 1 through an air guide seam 4 to form high-speed jet flow, and the high-speed jet flow impacts a compressor impeller 5 positioned on the inner side of the compressor casing 1 so as to enable the compressor impeller 5 to start rotating around a rotating shaft R, thereby realizing the air blowing starting of the gas turbine.
When the gas turbine works under variable working conditions, the annular airflow channel 3 in the gas turbine starting structure provided by the embodiment of the invention is extracted by the external fan, so that negative pressure is formed inside the annular airflow channel 3, and the air inside the compressor casing 1 is extracted to the annular airflow channel 3 through the air introducing seam 4, thereby achieving the purpose of stabilizing the working state of the compressor and enhancing the stability of the variable working conditions of the gas turbine.
Therefore, the gas turbine starting structure provided by the embodiment of the invention only needs to additionally arrange the bleed air channel casing 2 without excessively increasing the weight of the unit, and has the advantages of simple structure and portability. On the other hand, after the gas turbine is started, the structure still can play a role in enhancing the stability of the variable working condition of the gas turbine, so that the problem that the starting device of the gas turbine in the prior art cannot be reused is solved.
Further, in one embodiment, the compressor casing 1 further includes an air inlet 10 opening in the direction of the rotation axis R and an air inlet passage connected to the air inlet 10.
The compressor wheel 5 includes a blade airflow passage inlet 51 and a blade airflow passage outlet 52; the airflow enters the compressor wheel 5 through the blade airflow passage inlet 51, is pressurized by the compressor wheel 5, and is discharged through the blade airflow passage outlet 52.
In this embodiment, the compressor wheel 5 may cooperate with the compressor case 1 to control the tip clearance C formed by the two.
In one embodiment, the total cross-sectional area of the bleed slots 4 is smaller than the cross-sectional area of the annular airflow passage 3.
By making the total cross-sectional area of the bleed air gaps 4 smaller than the cross-sectional area of the annular airflow channel 3, the airflow can be continuously accelerated after entering the bleed air gaps 4 from the annular airflow channel 3, so that high-speed jet flow with higher strength is formed, and the starting efficiency of the gas turbine is improved.
Further, the number of the bleed air slots 4 is multiple and is arranged equidistantly along the circumferential direction of the compressor casing 1, as shown in fig. 2.
Through evenly setting up a plurality of bleed seams 4, can make the quantity of high-speed efflux show the increase, and make compressor impeller 5's atress more even to the stability and the efficiency of gas turbine start-up have further been improved.
Specifically, the number of the bleed air gaps 4 may be x — Nm, where N is a preset density coefficient, and m is the number of blades that the compressor wheel 5 has.
It will be appreciated that the greater the predetermined packing factor, the greater the number of bleed air slots 4 when the compressor wheel 5 has a given number of blades.
For example, in one embodiment, the value of N is 1.5. Of course, the specific size of the preset dense coefficient may be adjusted according to actual conditions, which is not limited in the embodiment of the present invention.
Further, the bleed slot 4 may include an inner opening 41 and an outer opening 42, the inner opening 41 facing the inside of the compressor case 1 and the outer opening 42 facing the annular airflow passage 3, as shown in fig. 4.
In one embodiment, as shown in FIGS. 1, 3 and 4, the height D of the bleed slot 4fComprises the following steps:
wherein D isiThe diameter of an air inlet 10 of a compressor casing 1; l is the axial width of the air-entraining slit 4 along the rotating shaft R; n is a radical of1A preset flow velocity coefficient is obtained; n is a radical of2Is a preset flow coefficient.
Wherein N is1May be the ratio of the flow rate of the air flow entering from the inner opening 41 to the flow rate of the air flow entering from the air intake 10, N2May be the ratio of the flow rate of the airflow entering from the inner opening 41 to the flow rate of the airflow entering from the intake port 10.
Of course, N1And N2The specific size of the first component may be redefined according to actual needs, and the embodiment of the present invention is not particularly limited in this regard.
The included angle theta between the inner opening 41 and the tangent of the inner wall surface of the compressor casing 1iComprises the following steps:
wherein D ismIs the minimum tip clearance between the compressor casing 1 and the compressor wheel 5.
The angle theta between the outer opening 42 and the tangent of the outer wall of the compressor case 1oComprises the following steps:
the height of the air guiding seam 4, the included angle between the inner opening 41 and the tangent line of the inner wall surface of the compressor casing 1 and the included angle between the outer opening 42 and the tangent line of the outer wall surface of the compressor casing 1 are determined, so that the arrangement angle and the position of the air guiding seam 4 can be accurately determined, and the specific implementation is facilitated.
On the basis of the above embodiments, as shown in fig. 3, the compressor casing 1 may be provided with a fitting surface 11 protruding outward to axially fit the bleed air passage casing 2, and the compressor casing 1 may be fixed to the bleed air passage casing 2 by a flange 12.
For example, the compressor casing 1 may be welded to the flange 12, and then the compressor casing 1 is fixed to the bleed air passage casing 2 via the flange 12.
The connection mode of the compressor casing 1 and the bleed air channel casing 2 does not need to destroy the integral structure of the compressor casing and the bleed air channel casing, and the connection is firm, so that the starting structure of the gas turbine can adapt to the working condition of high strength.
When the gas turbine is started, the annular airflow channel 3 in the gas turbine starting structure provided by the embodiment of the invention blows high-speed and high-pressure airflow from an external fan, the annular airflow channel 3 is relatively closed, and the airflow enters the outer opening 42 of the air guide slot 4 and flows from the annular airflow channel 3 to the inside of the compressor casing 1, as shown in fig. 5.
The total cross-sectional area of the bleed slots 4 is smaller than the cross-sectional area of the annular air flow passage 3 and the air flow continues to accelerate after flowing into the bleed slots 4, thereby forming a high velocity jet at the inner opening 41 of the bleed slots 4. The high-speed jet impacts the back of the blades of the compressor impeller 5 through the tip clearance C, so that the compressor impeller 5 starts to rotate around the rotation axis R. And after the impeller 5 of the gas compressor accelerates to a specific rotating speed, the external fan is disconnected, so that the blowing starting of the gas turbine is realized.
When the gas turbine works under variable working conditions, the annular airflow channel 3 in the gas turbine starting structure provided by the embodiment of the invention is extracted by an external fan, so that negative pressure is formed in the annular airflow channel 3. The pressure of the mainstream gas flow at the inner opening 41 of the bleed slot 4 is higher than the pressure at the outer opening 42 of the bleed slot 4. Part of the air flow passing through the tip clearance C flows from the inside of the compressor casing 1 to the annular air flow passage 3 through the air introduction slit 4, as shown in fig. 6.
When leakage flows occur at the blade tip position, the leakage flows do not flow from the pressure surface to the suction surface of the blade, and flow into the annular airflow channel 3 from the bleed air gap 4, and then are discharged to the environment.
In summary, the gas turbine starting structure provided by the embodiment of the invention starts the gas turbine by forming the high-speed jet flow in the bleed air seam 4 through acceleration to impact the back of the blade when the gas turbine is started. After the start is finished, the negative pressure state is presented in the annular airflow channel 3, the leakage flow at the blade tip is extracted, and the blockage of the compressor channel caused by the leakage flow is avoided, so that the aim of stabilizing the working state of the compressor is fulfilled, and the stability of the variable working condition of the gas turbine is improved.
Finally, it should be noted that: the above examples are only intended to illustrate the technical solution of the present invention, but not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.
Claims (10)
1. A gas turbine starting structure, comprising:
the compressor comprises a compressor casing (1), wherein a compressor impeller (5) is arranged on the inner side of the compressor casing (1), and the compressor impeller (5) rotates around a rotating shaft (R) positioned in the center of the inner side of the compressor casing (1);
the bleed air channel casing (2) is positioned outside the compressor casing (1) and is axially matched with the compressor casing (1) so as to form an annular bleed air channel (3) with the compressor casing (1);
the gas compressor casing (1) is circumferentially provided with a gas leading seam (4);
the compressor casing (1) further comprises: an air inlet (10) opening along the direction of the rotation axis R and an air inlet passage connected with the air inlet (10).
2. Gas turbine starting structure according to claim 1, wherein the total cross-sectional area of the gas introduction slits (4) is smaller than the cross-sectional area of the annular gas flow channel (3).
3. Gas turbine starting structure according to claim 2, wherein said bleed slots (4) are plural in number and are arranged equidistantly in the circumferential direction of said compressor casing (1).
4. A gas turbine starting structure according to claim 3, wherein the number of the bleed slots (4) is x Nm, where N is a preset packing factor and m is the number of blades the compressor wheel (5) has.
5. Gas turbine starting structure according to claim 4, wherein the gas introduction slit (4) comprises an inner opening (41) and an outer opening (42);
the inner opening (41) faces the inner side of the compressor casing (1), and the outer opening (42) faces the annular airflow channel (3).
6. Gas turbine starting structure according to claim 5, characterized in that the height D of the bleed air slot (4)fComprises the following steps:
wherein D isiThe diameter of an air inlet of a compressor casing; l is the axial width of the air-guiding slit (4) along the rotating shaft (R); n is a radical of1A preset flow velocity coefficient is obtained; n is a radical of2Is a preset flow coefficient.
7. Gas turbine starting structure according to claim 5, characterized in that the inner opening (41) forms an angle θ with the tangent of the inner wall surface of the compressor casing (1)iComprises the following steps:
wherein D ismIs the gap between the smallest leaves between the compressor casing (1) and the compressor impeller (5).
8. Gas turbine starting structure according to claim 7, characterized in that the angle θ of the outer opening (42) to the outer wall tangent of the compressor casing (1)oComprises the following steps:
9. gas turbine starting structure according to any of claims 1-8, characterised in that the compressor casing (1) is provided with a mating surface (11) projecting outwards for axial mating with the bleed air channel casing (2).
10. Gas turbine starting structure according to claim 9, characterized in that the compressor casing (1) and the bleed air channel casing (2) are fixed by means of a flange (12).
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| CN202010850918.0A CN111911288B (en) | 2020-08-21 | 2020-08-21 | Gas turbine starting structure |
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| CN202010850918.0A CN111911288B (en) | 2020-08-21 | 2020-08-21 | Gas turbine starting structure |
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| CN111911288A CN111911288A (en) | 2020-11-10 |
| CN111911288B true CN111911288B (en) | 2021-11-02 |
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| CN114526161B (en) * | 2022-04-22 | 2022-07-08 | 成都中科翼能科技有限公司 | Gas turbine's intermediary machine casket and reinforcement structure thereof |
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| CN103953560A (en) * | 2014-04-18 | 2014-07-30 | 合肥通用机械研究院 | Compressor expands steady system and is applied to compressor mechanism of this system |
| CN105782117A (en) * | 2016-03-07 | 2016-07-20 | 合肥通用机械研究院 | Stability extending device of centrifugal compressor |
| CN107524526A (en) * | 2017-08-31 | 2017-12-29 | 中国航发湖南动力机械研究所 | Compressor blowdown gas-turbine unit |
| CN108518355A (en) * | 2018-03-22 | 2018-09-11 | 清华大学 | A kind of reshaping compressor pumping casing |
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2020
- 2020-08-21 CN CN202010850918.0A patent/CN111911288B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103953560A (en) * | 2014-04-18 | 2014-07-30 | 合肥通用机械研究院 | Compressor expands steady system and is applied to compressor mechanism of this system |
| CN105782117A (en) * | 2016-03-07 | 2016-07-20 | 合肥通用机械研究院 | Stability extending device of centrifugal compressor |
| CN107524526A (en) * | 2017-08-31 | 2017-12-29 | 中国航发湖南动力机械研究所 | Compressor blowdown gas-turbine unit |
| CN108518355A (en) * | 2018-03-22 | 2018-09-11 | 清华大学 | A kind of reshaping compressor pumping casing |
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