CN205025581U - A heat preservation formula air intake system for gas turbine - Google Patents
A heat preservation formula air intake system for gas turbine Download PDFInfo
- Publication number
- CN205025581U CN205025581U CN201520649315.9U CN201520649315U CN205025581U CN 205025581 U CN205025581 U CN 205025581U CN 201520649315 U CN201520649315 U CN 201520649315U CN 205025581 U CN205025581 U CN 205025581U
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- China
- Prior art keywords
- air inlet
- main body
- inlet main
- gas turbine
- thermal insulating
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Abstract
The utility model discloses a heat preservation formula air intake system for gas turbine, it is unsatisfactory to solve current air intake system drying effect, and air intake system entry noise is big, the unsatisfactory technical problem of effect that just keeps warm, 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 includes interior heat preservation and external thermal insulation layer, be provided with air heat insulation layer between interior heat preservation and the external thermal insulation 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 multi -stage filtration ware and dehumidifier, the main part of admitting air in be provided with the muffler, the utility model has the advantages of simple structure, small in noise and keep warm effectually.
Description
Technical field
The utility model relates to technical field of mechanical equipment, relates to a kind of thermal insulating type gas handling system for gas turbine 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 the thermal insulating type gas handling system for gas turbine is one of most important subsidiary engine of gas turbine.
The existing thermal insulating type gas handling system purge drying effect for gas turbine is undesirable, and gas handling system ingress noise is large, and heat insulation effect is undesirable.
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 thermal insulating type gas handling system for gas turbine of sesame moisture content can be controlled.
The utility model to achieve these goals concrete by the following technical solutions:
A kind of thermal insulating type gas handling system for gas turbine, 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, thermal insulation layer comprises inner thermal insulating layer and external thermal insulation, air heat-insulation layer is provided with between described inner thermal insulating layer and external thermal insulation, 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 and dehumidifier near suction port place, is provided with baffler in described air inlet main body.
Further, described air inlet main body is arranged on supporting frame.
Further, described inner thermal insulating layer, external thermal insulation are aluminium silicate wool layer.
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.
The beneficial effects of the utility model are as follows:
The utility model structure is simple, the setting of baffler makes noise of equipment little, reduce noise pollution, air inlet main body is provided with thermal insulation layer along inwall, thermal insulation layer comprises inner thermal insulating layer and external thermal insulation, is provided with air heat-insulation layer between described inner thermal insulating layer and external thermal insulation, and this mechanism is arranged in rugged environment, this gas handling system is not subject to the impact of external environment, practical.
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 thermal insulating type gas handling system for gas turbine 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, 3-thermal insulation layer, 3-1-inner thermal insulating layer, 3-2-air barrier, 3-3-external thermal insulation, 4-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 thermal insulating type gas handling system for gas turbine, 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, thermal insulation layer 3 comprises inner thermal insulating layer 3-1 and external thermal insulation 3-3, air heat-insulation layer 3-2 is provided with between described inner thermal insulating layer 3-1 and external thermal insulation 3-3, 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 and dehumidifier 5 near suction port 1-1 place, baffler 4 is provided with in described air inlet main body 1.
Described air inlet main body 1 is arranged on supporting frame 8.
In the present embodiment, the setting of baffler 4 makes noise of equipment little, reduce noise unmanned, air inlet main body 1 is provided with thermal insulation layer 3 along inwall, thermal insulation layer 3 comprises inner thermal insulating layer 3-1 and external thermal insulation 3-3, is provided with air heat-insulation layer 3-2 between described inner thermal insulating layer 3-1 and external thermal insulation 3-3, and this mechanism is arranged in rugged environment, this gas handling system is not subject to the impact of external environment, practical.
Embodiment 2
As illustrated in fig. 1 and 2, the present embodiment provides a kind of thermal insulating type gas handling system for gas turbine, 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, thermal insulation layer 3 comprises inner thermal insulating layer 3-1 and external thermal insulation 3-3, air heat-insulation layer 3-2 is provided with between described inner thermal insulating layer 3-1 and external thermal insulation 3-3, 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 and dehumidifier 5 near suction port 1-1 place, baffler 4 is provided with in described air inlet main body 1.
Described air inlet main body 1 is arranged on supporting frame 8.
Described inner thermal insulating layer 3-1, external thermal insulation 3-3 are aluminium silicate wool layer.
Embodiment 3
The present embodiment provides as illustrated in fig. 1 and 2, the present embodiment provides a kind of thermal insulating type gas handling system for gas turbine, 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, thermal insulation layer 3 comprises inner thermal insulating layer 3-1 and external thermal insulation 3-3, air heat-insulation layer 3-2 is provided with between described inner thermal insulating layer 3-1 and external thermal insulation 3-3, 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 and dehumidifier 5 near suction port 1-1 place, baffler 4 is provided with in described air inlet main body 1.
Described air inlet main body 1 is arranged on supporting frame 8.
Described inner thermal insulating layer 3-1, external thermal insulation 3-3 are aluminium silicate wool layer.
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 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 (5)
1. the thermal insulating type gas handling system for gas turbine, 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, thermal insulation layer (3) comprises inner thermal insulating layer (3-1) and external thermal insulation (3-3), air heat-insulation layer (3-2) is provided with between described inner thermal insulating layer (3-1) and external thermal insulation (3-3), 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) and dehumidifier (5) near suction port (1-1) place, baffler (4) is provided with in described air inlet main body (1).
2. the thermal insulating type gas handling system for gas turbine according to claim 1, is characterized in that, described air inlet main body (1) is arranged on supporting frame (8).
3. the thermal insulating type gas handling system for gas turbine according to claim 1, is characterized in that, described inner thermal insulating layer (3-1), external thermal insulation (3-3) are aluminium silicate wool layer.
4. the thermal insulating type gas handling system for gas turbine 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).
5. the thermal insulating type gas handling system for gas turbine according to claim 4, 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).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520649315.9U CN205025581U (en) | 2015-08-26 | 2015-08-26 | A heat preservation formula air intake system for gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520649315.9U CN205025581U (en) | 2015-08-26 | 2015-08-26 | A heat preservation formula air intake system for gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205025581U true CN205025581U (en) | 2016-02-10 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520649315.9U Expired - Fee Related CN205025581U (en) | 2015-08-26 | 2015-08-26 | A heat preservation formula air intake system for gas turbine |
Country Status (1)
| Country | Link |
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| CN (1) | CN205025581U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105114180A (en) * | 2015-08-26 | 2015-12-02 | 成都博世德能源科技股份有限公司 | Heat preservation type air inlet system used for gas turbine |
-
2015
- 2015-08-26 CN CN201520649315.9U patent/CN205025581U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105114180A (en) * | 2015-08-26 | 2015-12-02 | 成都博世德能源科技股份有限公司 | Heat preservation type air inlet system used for gas turbine |
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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 |
Granted publication date: 20160210 Termination date: 20180826 |
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| CF01 | Termination of patent right due to non-payment of annual fee |