CN205025580U - Novel high -efficient gas turbine air intake system - Google Patents
Novel high -efficient gas turbine air intake system Download PDFInfo
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- CN205025580U CN205025580U CN201520649305.5U CN201520649305U CN205025580U CN 205025580 U CN205025580 U CN 205025580U CN 201520649305 U CN201520649305 U CN 201520649305U CN 205025580 U CN205025580 U CN 205025580U
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- main body
- air inlet
- gas turbine
- inlet main
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Abstract
The utility model discloses a novel high -efficient gas turbine air intake system, it is unsatisfactory to solve current air intake system drying effect, the applied unsatisfactory technical problem of low temperature environment, the utility model discloses a main part of admitting air, admit air the main part for the tubular structure, the main part of admitting air is provided with the heat preservation along the inner wall, the heat preservation form by a plurality of glass fiber layers and aluminium foil layer, the main part of admitting air includes air inlet and gas outlet, the air inlet on be provided with a plurality of intake pipe, the inside air inlet department of being close to of main part of admitting air be provided with the multi -stage filtration ware, the main part of admitting air in be provided with the muffler, the main part of admitting air in arranged a plurality of steam sources, the utility model has the advantages of simple structure, small in noise and low temperature environment application effect are good.
Description
Technical field
The utility model relates to technical field of mechanical equipment, relates to a kind of new and effective gas turbine inlet air system more specifically.
Background technique
Gas turbine is for working medium impeller High Rotation Speed with the gas of continuous-flow, it is the internal combustion type dynamic power machine of useful work by the energy conversion of fuel, it is a kind of rotary vane type heat engine, in the main flow of air and combustion gas, primarily of this three large parts composition gas turbine cycle of gas compressor, firing chamber and combustion gas turbine.
The combustion air of gas turbine must carry out the process such as purified treatment, dry process before being introduced into gas compressor, and new and effective gas turbine inlet air system is one of most important subsidiary engine of gas turbine.
Existing new and effective gas turbine inlet air system purification drying effect is undesirable, gas handling system ingress noise is large, and heat insulation effect is undesirable, the air entering system at low temperature environment occurs freezing and affects filter efficiency and to freeze on filter core or affect gas compressor performance characteristic icing on compressor inlet blade.How to solve above technical problem and become the striving direction of those skilled in the art.
Model utility content
The utility model in order to overcome above-mentioned technical deficiency, design a kind of structure simple, can increase work efficiency, ensure product first in first out, the new and effective gas turbine inlet air system of sesame moisture content can be controlled.
The utility model to achieve these goals concrete by the following technical solutions:
A kind of new and effective gas turbine inlet air system, comprise air inlet main body, described air inlet main body is tubular structure, air inlet main body is provided with thermal insulation layer along inwall, described thermal insulation layer is made up of some glass fibre layers and aluminium foil layer, described air inlet main body comprises suction port and air outlet, described suction port is provided with some suction tude, described air inlet body interior is provided with multistage filter near suction port place, be provided with baffler in described air inlet main body, in described air inlet main body, be furnished with multiple hot gas source.
Further, described air inlet main body is arranged on supporting frame.
Further, described glass fibre layer and each 10 layers of aluminium foil layer, glass fibre layer and aluminium foil layer are overlapping, and adjacent two layers aluminium foil layer does not contact.
Further, the thickness of described glass fibre layer is 0.1 ~ 35mm, and the thickness of described aluminium foil layer is 0.2 ~ 0.4mm.
Further, described multistage filter comprises the one-level filter core, secondary filter core and the three grades of filter cores that inwardly set gradually from suction port.
Further, the filtering hole aperture of described one-level filter core is greater than the filtering hole aperture of described three grades of filter cores; The filtering hole aperture of described secondary filter core is between described one-level filter core and the filtering hole aperture of described three grades of filter cores.
Further, the number of described hot gas source 2 is 3.
Further, in described air inlet main body, multistage filter place is provided with dehumidifier.
The beneficial effects of the utility model are as follows:
The utility model structure is simple, and air inlet main body is provided with thermal insulation layer along inwall, and thermal insulation layer is made up of some glass fibre layers and aluminium foil layer, and this mechanism is arranged in rugged environment, and this gas handling system is not subject to the impact of external environment, practical; Multiple hot gas sources in air inlet main body, hot gas source is arranged in gas handling system, this thermal source be arranged on the lower operating mode of external temperature under, effectively can prevent the air of the system of entering from occurring freezing and affecting filter efficiency (freezing on filter core) or affect gas compressor performance characteristic (freezing on compressor inlet blade), have good prospect at low temperature environment.
Filter adopts multistage filtering both to ensure that the degree of purity entering gas in gas turbine, protects multi-stage filter core again simultaneously.Extend the working life of filter.
Accompanying drawing explanation
The structural representation of a kind of new and effective gas turbine inlet air system of Fig. 1 the utility model;
Fig. 2 heat insulation layer structure schematic diagram;
Reference character: 1-air inlet main body, 1-1-suction port, 1-2-air outlet, 2-hot gas source, 3-thermal insulation layer, 3-1-glass fibre layer, 3-2-aluminium foil layer, 4-has baffler, 5-dehumidifier, 6-multistage filter, 6-1-one-level filter core, 6-2-secondary filter core, 6-3-tri-grades of filter cores, 7-suction tude, 8-supporting frame.
Embodiment
In order to those skilled in the art person better understands the utility model, below in conjunction with accompanying drawing, embodiment is described in further detail the utility model.
Embodiment 1
As shown in Figure 1, the present embodiment provides a kind of new and effective gas turbine inlet air system, comprise air inlet main body 1, described air inlet main body 1 is tubular structure, air inlet main body 1 is provided with thermal insulation layer 3 along inwall, described thermal insulation layer 3 is made up of some glass fibre layer 3-1 and aluminium foil layer 3-2, described air inlet main body 1 comprises suction port 1-1 and air outlet 1-2, described suction port 1-1 is provided with some suction tude 7, described air inlet main body 1 is inner is provided with multistage filter 6 near suction port 1-1 place, baffler 4 is provided with in described air inlet main body 1, multiple hot gas source 2 is furnished with in described air inlet main body 1.
Described air inlet main body 1 is arranged on supporting frame 8.
In the present embodiment, air inlet main body 1 is provided with thermal insulation layer 3 along inwall, thermal insulation layer 3 is made up of some glass fibre layer 3-1 and aluminium foil layer 3-2, this mechanism is arranged in rugged environment, this gas handling system is not subject to the impact of external environment, practical, hot gas source 2 is arranged in gas handling system, under the operating mode that external temperature is lower, effectively can prevent the air of the system of entering from occurring freezing and affecting filter efficiency (freezing on filter core) or affect gas compressor performance characteristic (freezing on compressor inlet blade), have good prospect at low temperature environment.
Embodiment 2
As illustrated in fig. 1 and 2, the present embodiment provides a kind of new and effective gas turbine inlet air system, comprise air inlet main body 1, described air inlet main body 1 is tubular structure, air inlet main body 1 is provided with thermal insulation layer 3 along inwall, described thermal insulation layer 3 is made up of some glass fibre layer 3-1 and aluminium foil layer 3-2, described air inlet main body 1 comprises suction port 1-1 and air outlet 1-2, described suction port 1-1 is provided with some suction tude 7, described air inlet main body 1 is inner is provided with multistage filter 6 near suction port 1-1 place, baffler 4 is provided with in described air inlet main body 1, multiple hot gas source 2 is furnished with in described air inlet main body 1.
Each 10 layers of described glass fibre layer 3-1 and aluminium foil layer 3-2, glass fibre layer 3-1 and aluminium foil layer 3-2 is overlapping, and adjacent two layers aluminium foil layer 3-2 does not contact.
The thickness of described glass fibre layer 3-1 is 0.1 ~ 35mm, and the thickness of described aluminium foil layer 3-2 is 0.2 ~ 0.4mm.
Embodiment 3
The present embodiment provides a kind of new and effective gas turbine inlet air system, comprise air inlet main body 1, described air inlet main body 1 is tubular structure, air inlet main body 1 is provided with thermal insulation layer 3 along inwall, described thermal insulation layer 3 is made up of some glass fibre layer 3-1 and aluminium foil layer 3-2, described air inlet main body 1 comprises suction port 1-1 and air outlet 1-2, described suction port 1-1 is provided with some suction tude 7, described air inlet main body 1 is inner is provided with multistage filter 6 near suction port 1-1 place, baffler 4 is provided with in described air inlet main body 1, multiple hot gas source 2 is furnished with in described air inlet main body 1.
The number of described hot gas source 2 is 3.
Described multistage filter 6 comprises one-level filter core 6-1, secondary filter core 6-2 and the three grade filter core 6-3 inwardly set gradually from suction port 1-1.
The filtering hole aperture of described one-level filter core 6-1 is greater than the filtering hole aperture of described three grades of filter core 6-3; The filtering hole aperture of described secondary filter core 6-2 is between described one-level filter core 6-1 and the filtering hole aperture of described three grades of filter core 6-3.
In described air inlet main body 1, multistage filter 6 place is provided with dehumidifier 5.
In the present embodiment, gas, after one-level filter core 6-1, secondary filter core 6-2 and the three grade filter core 6-3 of multistage filter 6, both ensure that the degree of purity entering gas in gas turbine, protected multi-stage filter core again simultaneously, extended the working life of filter.
The above; be only preferred embodiment of the present utility model; not in order to limit the utility model; scope of patent protection of the present utility model is as the criterion with claims; the equivalent structure change that every utilization specification of the present utility model and accompanying drawing content are done, in like manner all should be included in protection domain of the present utility model.
Claims (8)
1. a new and effective gas turbine inlet air system, comprise air inlet main body (1), it is characterized in that, described air inlet main body (1) is tubular structure, air inlet main body (1) is provided with thermal insulation layer (3) along inwall, described thermal insulation layer (3) is made up of some glass fibre layers (3-1) and aluminium foil layer (3-2), described air inlet main body (1) comprises suction port (1-1) and air outlet (1-2), described suction port (1-1) is provided with some suction tude (7), described air inlet main body (1) is inner is provided with multistage filter (6) near suction port (1-1) place, baffler (4) is provided with in described air inlet main body (1), multiple hot gas source (2) is furnished with in described air inlet main body (1).
2. new and effective gas turbine inlet air system according to claim 1, is characterized in that, described air inlet main body (1) is arranged on supporting frame (8).
3. new and effective gas turbine inlet air system according to claim 1, it is characterized in that, described glass fibre layer (3-1) and each 10 layers of aluminium foil layer (3-2), glass fibre layer (3-1) and aluminium foil layer (3-2) are overlapping, and adjacent two layers aluminium foil layer 3-2 does not contact.
4. new and effective gas turbine inlet air system according to claim 3, is characterized in that, the thickness of described glass fibre layer (3-1) is 0.1 ~ 35mm, and the thickness of described aluminium foil layer (3-2) is 0.2 ~ 0.4mm.
5. new and effective gas turbine inlet air system according to claim 1, it is characterized in that, described multistage filter (6) comprise inwardly set gradually from suction port (1-1) one-level filter core (6-1), secondary filter core (6-2) and three grades of filter cores (6-3).
6. new and effective gas turbine inlet air system according to claim 5, is characterized in that, the filtering hole aperture of described one-level filter core (6-1) is greater than the filtering hole aperture of described three grades of filter cores (6-3); The filtering hole aperture of described secondary filter core (6-2) is between described one-level filter core (6-1) and the filtering hole aperture of described three grades of filter cores (6-3).
7. new and effective gas turbine inlet air system according to claim 1, is characterized in that, the number of described hot gas source (2) is 3.
8. new and effective gas turbine inlet air system according to claim 1, is characterized in that, in described air inlet main body (1), multistage filter (6) place is provided with dehumidifier (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520649305.5U CN205025580U (en) | 2015-08-26 | 2015-08-26 | Novel high -efficient gas turbine air intake system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520649305.5U CN205025580U (en) | 2015-08-26 | 2015-08-26 | Novel high -efficient gas turbine air intake system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205025580U true CN205025580U (en) | 2016-02-10 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520649305.5U Expired - Fee Related CN205025580U (en) | 2015-08-26 | 2015-08-26 | Novel high -efficient gas turbine air intake system |
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| Country | Link |
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| CN (1) | CN205025580U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105089786A (en) * | 2015-08-26 | 2015-11-25 | 成都博世德能源科技股份有限公司 | Novel efficient air intake system of gas turbine |
| CN108661804A (en) * | 2018-04-28 | 2018-10-16 | 江苏华强新能源科技有限公司 | A kind of energy-saving high-efficient gas turbine gas handling system |
-
2015
- 2015-08-26 CN CN201520649305.5U patent/CN205025580U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105089786A (en) * | 2015-08-26 | 2015-11-25 | 成都博世德能源科技股份有限公司 | Novel efficient air intake system of gas turbine |
| CN108661804A (en) * | 2018-04-28 | 2018-10-16 | 江苏华强新能源科技有限公司 | A kind of energy-saving high-efficient gas turbine gas handling system |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160210 Termination date: 20180826 |