CN105114180A - Heat preservation type air inlet system used for gas turbine - Google Patents
Heat preservation type air inlet system used for gas turbine Download PDFInfo
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- CN105114180A CN105114180A CN201510529500.9A CN201510529500A CN105114180A CN 105114180 A CN105114180 A CN 105114180A CN 201510529500 A CN201510529500 A CN 201510529500A CN 105114180 A CN105114180 A CN 105114180A
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- air inlet
- main body
- heat preservation
- inlet main
- gas turbine
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Abstract
The invention discloses a heat preservation type air inlet system used for a gas turbine. The heat preservation type air inlet system used for the gas turbine aims at solving the technical problems that in an existing air inlet system, the drying effect is not ideal, the noise at an inlet of the air inlet system is high, and the heat preservation effect is not ideal. The heat preservation type air inlet system comprises an air inlet body; the air inlet body is of a tubular structure; a heat preservation layer is arranged along the inner wall of the air inlet body; the heat preservation layer comprises an inner heat preservation layer and an outer heat preservation layer; an air heat insulation layer is arranged between the inner heat preservation layer and the outer heat preservation layer; the air inlet body comprises an air inlet and an air outlet; a plurality of air inlet pipes are arranged on the air inlet; a multistage filter and a dehumidifier are arranged on the portion, close to the air inlet, inside the air inlet body; a silencer is arranged inside the air inlet body. The heat preservation type air inlet system has the advantages of being simple in structure, low in noise and good in heat preservation effect.
Description
Technical field
The present invention relates to technical field of mechanical equipment, relate to a kind of thermal insulating type gas handling system for gas turbine more specifically.
Background technique
Gas turbine is for working medium drives with the gas of continuous-flow
impellerhigh Rotation Speed, being the internal combustion type dynamic power machine of useful work by the energy conversion of fuel, 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.
Summary of the invention
The present invention 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 present invention 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.
Beneficial effect of the present invention is as follows:
Structure of the present invention 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 present invention;
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 present invention, below in conjunction with accompanying drawing, embodiment is described in further detail the present invention.
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 invention, not in order to limit the present invention, scope of patent protection of the present invention is as the criterion with claims; the equivalent structure change that every utilization specification of the present invention and accompanying drawing content are done, in like manner all should be included in protection scope of the present invention.
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 |
|---|---|---|---|
| CN201510529500.9A CN105114180A (en) | 2015-08-26 | 2015-08-26 | Heat preservation type air inlet system used for gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510529500.9A CN105114180A (en) | 2015-08-26 | 2015-08-26 | Heat preservation type air inlet system used for gas turbine |
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| Publication Number | Publication Date |
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| CN105114180A true CN105114180A (en) | 2015-12-02 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201510529500.9A Pending CN105114180A (en) | 2015-08-26 | 2015-08-26 | Heat preservation type air inlet system used for gas turbine |
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| CN (1) | CN105114180A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107503849A (en) * | 2017-10-23 | 2017-12-22 | 江苏华强新能源科技有限公司 | A kind of high-efficiency gas turbine frost prevention gas handling system |
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| US4047379A (en) * | 1976-04-28 | 1977-09-13 | General Electric Company | Transient air temperature sensing system |
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| US20080178571A1 (en) * | 2007-01-31 | 2008-07-31 | Power Systems Manufacturing, Llc | Inlet Bleed Heat and Power Augmentation For A Gas Turbine Engine |
| EP2343401A1 (en) * | 2009-12-22 | 2011-07-13 | Rolls-Royce plc | Hydrophobic surface |
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| CN205025581U (en) * | 2015-08-26 | 2016-02-10 | 成都博世德能源科技股份有限公司 | A heat preservation formula air intake system for gas turbine |
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2015
- 2015-08-26 CN CN201510529500.9A patent/CN105114180A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4047379A (en) * | 1976-04-28 | 1977-09-13 | General Electric Company | Transient air temperature sensing system |
| CN87100757A (en) * | 1987-02-20 | 1988-08-31 | 4.4工程工业工厂 | Laminar heat shield |
| US20080178571A1 (en) * | 2007-01-31 | 2008-07-31 | Power Systems Manufacturing, Llc | Inlet Bleed Heat and Power Augmentation For A Gas Turbine Engine |
| EP2343401A1 (en) * | 2009-12-22 | 2011-07-13 | Rolls-Royce plc | Hydrophobic surface |
| CN203879632U (en) * | 2014-05-08 | 2014-10-15 | 中国联合工程公司 | Inlet gas rectifying device for large-size combustion gas turbine |
| CN104295859A (en) * | 2014-10-15 | 2015-01-21 | 航天晨光股份有限公司 | Efficient pre-generated steam heat insulating tube |
| CN205025581U (en) * | 2015-08-26 | 2016-02-10 | 成都博世德能源科技股份有限公司 | A heat preservation formula air intake system for gas turbine |
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| 张楹等: "西门子SGT5-4000F型燃气轮机进气系统简介", 《热力透平》 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107503849A (en) * | 2017-10-23 | 2017-12-22 | 江苏华强新能源科技有限公司 | A kind of high-efficiency gas turbine frost prevention gas handling system |
| CN107503849B (en) * | 2017-10-23 | 2023-12-05 | 江苏华强新能源科技有限公司 | Efficient gas turbine frost prevention air inlet system |
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Application publication date: 20151202 |