CN212428956U - Lower end wall structure of power turbine of medium and small combustion engines for power generation - Google Patents
Lower end wall structure of power turbine of medium and small combustion engines for power generation Download PDFInfo
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- CN212428956U CN212428956U CN202021197019.7U CN202021197019U CN212428956U CN 212428956 U CN212428956 U CN 212428956U CN 202021197019 U CN202021197019 U CN 202021197019U CN 212428956 U CN212428956 U CN 212428956U
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Abstract
A lower end wall structure of a power turbine of a medium and small gas turbine for power generation belongs to the field of gas turbine power turbines. The utility model provides a current well small gas turbine power turbine structure complicated, sealed effect is poor, the problem of power turbine aerodynamic inefficiency. The utility model discloses a first order stationary blade, first order moving blade, second level stationary blade, second level moving blade, third level stationary blade, third level moving blade, fourth level stationary blade and fourth level moving blade, first sealed passageway has between first order stationary blade and the first order moving blade, and first order moving blade constitutes the sealed passageway of second with the lower terminal wall of second level stationary blade, constitutes corresponding sealed passageway between each moving blade and the stationary blade respectively. The utility model discloses simple structure, it is sealed effectual, through the sealed clearance between each sound leaf of control effectively improved power turbine's pneumatic efficiency.
Description
Technical Field
The utility model relates to a terminal wall structure under small and medium-sized gas turbine power turbine for electricity generation belongs to gas turbine power turbine field.
Background
At present, for a unit for generating power by a medium and small gas turbine, the general stage number is more than or equal to 3, an effective method for improving the cycle efficiency of the power turbine is to improve the stage number of the power turbine, the improvement of the turbine efficiency not only needs advanced blade design, but also needs reasonable design of a lower end wall and a connecting structure thereof, at present, the design of a sealing structure of the lower end wall and a disk cavity of the power turbine of the medium and small gas turbine for generating power is not provided, the lower end wall of the power turbine of the existing medium and small gas turbine has a complex structure and is difficult to assemble, disassemble and maintain, and the sealing effect of the disk cavity is poor, so;
in summary, a lower end wall structure of a power turbine of a medium and small combustion engine for power generation, which has a simple structure and a good sealing effect, is needed to solve the above problems.
SUMMERY OF THE UTILITY MODEL
The utility model discloses a solve the current middle and small combustion engine power turbine lower extreme wall structure complicated, the poor problem of sealed effect, the utility model discloses a "middle and small combustion engine power turbine lower extreme wall structure for electricity generation". 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 lower end wall structure of a power turbine of a small and medium-sized combustion engine for power generation comprises a first-stage stationary blade, a first-stage moving blade, a second-stage stationary blade, a second-stage moving blade, a third-stage stationary blade, a third-stage moving blade, a fourth-stage stationary blade and a fourth-stage moving blade, the first sealing channel is arranged between the first-stage static blades and the first-stage moving blades, the first-stage moving blades and the lower end walls of the second-stage static blades form a second sealing channel, the second-stage static blades and the lower end walls of the second-stage moving blades form a third sealing channel, the third-stage static blades and the lower end walls of the second-stage moving blades form a fourth sealing channel, the third-stage static blades and the lower end walls of the third-stage moving blades form a fifth sealing channel, the fourth-stage static blades and the lower end walls of the third-stage moving blades form a sixth sealing channel, and the fourth-stage static blades and the lower end walls of the fourth-stage moving blades form a seventh sealing channel.
Furthermore, the lower end wall of the second-stage stationary blade is connected with a connecting piece, and the first disc cavity sealing structure is connected with the connecting piece through a bolt.
Further, the clearance L5 of the first disk cavity sealing structure is in the range of 0.9mm-1.2 mm.
Furthermore, the lower end wall of the third-stage stationary blade is connected with a second connecting sheet, and the second disc cavity sealing structure is connected with the second connecting sheet through a second bolt.
Further, the clearance L10 of the second disc cavity sealing mechanism is in the range of 0.4mm-0.6 mm.
Furthermore, the lower end wall of the fourth stage stationary blade is connected with a third connecting piece, and the third disc cavity sealing structure is connected with the third connecting piece through a third bolt.
Further, the clearance L16 of the third disc cavity mechanism is in the range of 0.4mm-0.6 mm.
Further, the first sealing channel 2 comprises a first sealing gap L1, a first outlet sealing gap L2, the first sealing gap L1 is in the range of 4.5mm-5.2mm, and the first outlet sealing gap L2 is in the range of 7.2mm-8.2 mm;
the second seal channel 24 comprises a second seal gap L3 and a second outlet seal gap L4, the second seal gap L3 ranges between 2.0mm and 2.4mm, the second outlet seal gap L4 ranges between 6mm and 6.5 mm;
the third seal channel 25 comprises a third seal gap L6 and a third outlet seal gap L7, the third seal gap L6 ranges between 5.0mm and 5.5mm, and the third outlet seal gap L7 ranges between 3.0mm and 3.5 mm;
the fourth seal channel 26 comprises a fourth seal gap L8 and a fourth outlet seal gap L9, the fourth seal gap L8 ranges between 2.0mm and 2.4mm, the fourth outlet seal gap L9 ranges between 6.0mm and 6.5 mm;
the fifth sealing channel 27 comprises a fifth sealing gap L11 and a fifth outlet sealing gap L12, the fifth sealing gap L11 ranges between 5.0mm and 5.5mm, the fifth outlet sealing gap L12 ranges between 6.0mm and 6.5 mm;
the sixth seal channel 28 comprises a sixth seal gap L14 and a sixth outlet seal gap L15, the sixth seal gap L14 ranges between 2.0mm and 2.3mm, the sixth outlet seal gap L15 ranges between 6.0mm and 6.5 mm;
the seventh sealing channel 29 includes a seventh sealing gap L17 and a seventh outlet sealing gap L18, the seventh sealing gap L17 ranges between 5.0mm and 5.5mm, and the seventh outlet sealing gap L18 ranges between 6.0mm and 6.5mm
The utility model has the advantages that:
1. by controlling the clearance between the moving blade and the static blade and the sealing clearance between the disc cavities, the main channel gas is effectively organized to enter the rotor, and the pneumatic efficiency is improved;
2. the lower end wall connecting structure of the power turbine is simple and convenient to disassemble, assemble and maintain;
3. the turbine efficiency is improved while sealing is met by setting different sealing gaps, and meanwhile, the sealing pressure and the sealing air quantity of the front and rear stages of the distribution disc cavity are adjusted through the gaps sealed by the comb teeth, so that the safe operation of the unit is ensured.
Drawings
FIG. 1 is a general schematic diagram of a lower end wall structure of a power turbine of a small and medium-sized combustion engine for power generation.
In the figure, 1-first stage stationary blades, 2-first stage sealing channels, 3-first stage moving blades, 4-second stage stationary blades, 5-first disk cavity sealing structures, 6-second stage moving blades, 7-connecting pieces, 8-bolts, 9-third stage stationary blades, 12-second bolts, 13-second connecting pieces, 15-second disk cavity sealing structures, 16-third stage moving blades, 17-fourth stage stationary blades, 20-third disk cavity sealing structures, 21-third bolts, 22-third connecting pieces, 23-fourth stage moving blades, 24-second sealing channels, 25-third sealing channels, 26-fourth sealing channels, 27-fifth sealing channels, 28-sixth sealing channels and 29-seventh sealing channels.
Detailed Description
In order to make the objects, solutions and advantages of the present invention more apparent, the present invention will be described with reference to 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 present embodiment is described with reference to fig. 1, and the lower end wall structure of a small-sized power turbine for power generation of the present embodiment includes a first stage stationary blade 1, a first stage moving blade 3, a second stage stationary blade 4, a second stage moving blade 6, a third stage stationary blade 9, a third stage moving blade 16, a fourth stage stationary blade 17, and a fourth stage moving blade 23, wherein a first seal passage 2 is provided between the first stage stationary blade 1 and the first stage moving blade 3, a second seal passage 24 is provided between the first stage moving blade 3 and the lower end wall of the second stage stationary blade 4, a third seal passage 25 is provided between the second stage stationary blade 4 and the lower end wall of the second stage moving blade 6, a fourth seal passage 26 is provided between the third stage stationary blade 9 and the lower end wall of the second stage moving blade 6, a fifth seal passage 27 is provided between the third stage stationary blade 9 and the lower end wall of the third stage moving blade 16, a sixth seal passage 28 is provided between the fourth stage stationary blade 17 and the lower end, the fourth stage stationary blades 17 and the lower end walls of the fourth stage moving blades 23 form seventh seal passages 29; the dynamic and static blades adopt reasonable sealing gap design, the main channel gas is effectively organized to enter the rotor, and the pneumatic efficiency is improved.
The second embodiment is as follows: referring to fig. 1, the present embodiment is described, and a lower end wall structure of a power turbine of a small and medium-sized power generation internal combustion engine of the present embodiment is characterized in that a lower end wall of the second-stage stationary blades 4 is connected with a connecting piece 7, and a first disk cavity sealing structure 5 is connected with the connecting piece 7 through bolts 8;
specifically, the clearance L5 of the first disc cavity sealing structure 5 is in the range of 0.9mm-1.2 mm;
specifically, the lower end wall of the third-stage stationary blade 9 is connected with a second connecting sheet 13, and the second disc cavity sealing structure 15 is connected with the second connecting sheet 13 through a second bolt 12;
specifically, the clearance L10 of the second disc cavity sealing mechanism 15 is in the range of 0.4mm-0.6 mm;
specifically, the lower end wall of the fourth stage stationary blade 17 is connected with a third connecting piece 22, and the third disc cavity sealing structure 20 is connected with the third connecting piece 22 through a third bolt 21;
specifically, the clearance L16 of the third disc cavity sealing structure 20 is in the range of 0.4mm-0.6 mm; pressure and tolerance around each dish chamber seal structure can balance can make the unit reach high-efficient safe operation, through the sealed clearance of control dish chamber seal structure, improves power turbine's pneumatic efficiency, and the sealed tolerance of each reasonable distribution of dish chamber seal structure makes power turbine can reach high-efficient pneumatic efficiency and reach the inside effect of sealed rotor, reduces adapting unit simultaneously.
The third concrete implementation mode: the lower end wall structure of the power turbine of the small and medium-sized combustion engine for power generation of the embodiment is described by combining with fig. 1, the first seal passage 2 of the embodiment comprises a first seal gap L1 and a first outlet seal gap L2, the first seal gap L1 ranges from 4.5mm to 5.2mm, and the first outlet seal gap L2 ranges from 7.2mm to 8.2 mm;
the second seal channel 24 comprises a second seal gap L3 and a second outlet seal gap L4, the second seal gap L3 ranges between 2.0mm and 2.4mm, the second outlet seal gap L4 ranges between 6mm and 6.5 mm;
the third seal channel 25 comprises a third seal gap L6 and a third outlet seal gap L7, the third seal gap L6 ranges between 5.0mm and 5.5mm, and the third outlet seal gap L7 ranges between 3.0mm and 3.5 mm;
the fourth seal channel 26 comprises a fourth seal gap L8 and a fourth outlet seal gap L9, the fourth seal gap L8 ranges between 2.0mm and 2.4mm, the fourth outlet seal gap L9 ranges between 6.0mm and 6.5 mm;
the fifth sealing channel 27 comprises a fifth sealing gap L11 and a fifth outlet sealing gap L12, the fifth sealing gap L11 ranges between 5.0mm and 5.5mm, the fifth outlet sealing gap L12 ranges between 6.0mm and 6.5 mm;
the sixth seal channel 28 comprises a sixth seal gap L14 and a sixth outlet seal gap L15, the sixth seal gap L14 ranges between 2.0mm and 2.3mm, the sixth outlet seal gap L15 ranges between 6.0mm and 6.5 mm;
the seventh sealing channel 29 comprises a seventh sealing gap L17 and a seventh outlet sealing gap L18, the seventh sealing gap L17 ranges between 5.0mm and 5.5mm, the seventh outlet sealing gap L18 ranges between 6.0mm and 6.5 mm; the gap design in the range is adopted between the moving blades and the static blades, so that the main channel gas can be effectively organized to enter the rotor, the pneumatic efficiency of the power turbine is improved, and the unit can efficiently run.
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 (8)
1. The utility model provides a middle and small combustion engine power turbine lower extreme wall structure for electricity generation which characterized in that: the turbine blade sealing device comprises a first-stage stationary blade (1), a first-stage moving blade (3), a second-stage stationary blade (4), a second-stage moving blade (6), a third-stage stationary blade (9), a third-stage moving blade (16), a fourth-stage stationary blade (17) and a fourth-stage moving blade (23), wherein a first sealing channel (2) is arranged between the first-stage stationary blade (1) and the first-stage moving blade (3), the first-stage moving blade (3) and the lower end wall of the second-stage stationary blade (4) form a second sealing channel (24), the second-stage stationary blade (4) and the lower end wall of the second-stage stationary blade (6) form a third sealing channel (25), the third-stage stationary blade (9) and the lower end wall of the second-stage moving blade (6) form a fourth sealing channel (26), and the third-stage stationary blade (9) and the lower end wall of the third-stage moving blade (16, the lower end walls of the fourth stage stationary blades (17) and the third stage moving blades (16) form a sixth seal passage (28), and the lower end walls of the fourth stage stationary blades (17) and the fourth stage moving blades (23) form a seventh seal passage (29).
2. The lower end wall structure of the power turbine of the small and medium-sized combustion engine for power generation as claimed in claim 1, wherein: the lower end wall of the second-stage stationary blade (4) is connected with a connecting piece (7), and the first disc cavity sealing structure (5) is connected with the connecting piece (7) through a bolt (8).
3. The lower end wall structure of the power turbine of the small and medium-sized combustion engine for power generation as claimed in claim 2, wherein: the clearance L5 of the first disc cavity sealing structure (5) is in the range of 0.9mm-1.2 mm.
4. The lower end wall structure of the power turbine of the small and medium-sized combustion engine for power generation as claimed in claim 1, wherein: the lower end wall of the third-stage stationary blade (9) is connected with a second connecting piece (13), and the second disc cavity sealing structure (15) is connected with the second connecting piece (13) through a second bolt (12).
5. The lower end wall structure of the power turbine of the small and medium-sized combustion engine for power generation as claimed in claim 4, wherein: the clearance L10 of the second disc cavity sealing structure (15) is in the range of 0.4mm-0.6 mm.
6. The lower end wall structure of the power turbine of the small and medium-sized combustion engine for power generation as claimed in claim 1, wherein: the lower end wall of the fourth-stage stationary blade (17) is connected with a third connecting piece (22), and the third disc cavity sealing structure (20) is connected with the third connecting piece (22) through a third bolt (21).
7. The lower end wall structure of the power turbine of the small and medium-sized combustion engine for power generation as claimed in claim 6, wherein: the clearance L16 of the third disc cavity sealing structure (20) is in the range of 0.4mm-0.6 mm.
8. The lower end wall structure of the power turbine of the small and medium-sized combustion engine for power generation as claimed in claim 1, wherein: the first sealing channel (2) comprises a first sealing gap L1, a first outlet sealing gap L2, the first sealing gap L1 ranges between 4.5mm-5.2mm, the first outlet sealing gap L2 ranges between 7.2mm-8.2 mm;
the second seal channel (24) comprises a second seal gap L3 and a second outlet seal gap L4, the second seal gap L3 ranges between 2.0mm-2.4mm, the second outlet seal gap L4 ranges between 6mm-6.5 mm;
the third seal channel (25) comprises a third seal gap L6 and a third outlet seal gap L7, the third seal gap L6 ranges between 5.0mm-5.5mm, the third outlet seal gap L7 ranges between 3.0mm-3.5 mm;
the fourth seal channel (26) comprises a fourth seal gap L8 and a fourth outlet seal gap L9, the fourth seal gap L8 ranges between 2.0mm-2.4mm, the fourth outlet seal gap L9 ranges between 6.0mm-6.5 mm;
the fifth sealing channel (27) comprises a fifth sealing gap L11 and a fifth outlet sealing gap L12, the fifth sealing gap L11 ranges between 5.0mm-5.5mm, the fifth outlet sealing gap L12 ranges between 6.0mm-6.5 mm;
the sixth sealing channel (28) comprises a sixth sealing gap L14 and a sixth outlet sealing gap L15, the sixth sealing gap L14 ranges between 2.0mm-2.3mm, the sixth outlet sealing gap L15 ranges between 6.0mm-6.5 mm;
the seventh sealing channel (29) comprises a seventh sealing gap L17 and a seventh outlet sealing gap L18, the seventh sealing gap L17 ranging between 5.0mm-5.5mm and the seventh outlet sealing gap L18 ranging between 6.0mm-6.5 mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021197019.7U CN212428956U (en) | 2020-06-24 | 2020-06-24 | Lower end wall structure of power turbine of medium and small combustion engines for power generation |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021197019.7U CN212428956U (en) | 2020-06-24 | 2020-06-24 | Lower end wall structure of power turbine of medium and small combustion engines for power generation |
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| CN212428956U true CN212428956U (en) | 2021-01-29 |
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| CN202021197019.7U Active CN212428956U (en) | 2020-06-24 | 2020-06-24 | Lower end wall structure of power turbine of medium and small combustion engines for power generation |
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| CN (1) | CN212428956U (en) |
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