CN117685097A - Cabin ventilation system suitable for aero-retrofit gas turbine and aero-retrofit gas turbine - Google Patents

Abstract

The invention provides a cabin ventilation system suitable for a aero-modified gas turbine and the aero-modified gas turbine, belonging to the technical field of aero-modified gas turbine equipment. The air inlet filter chamber component passes through the cabin ventilation and combustion-supporting air inlet chamber and is communicated with the engine room component through a plurality of pipelines, the cabin ventilation and combustion-supporting air inlet chamber is connected with the engine room component through a cabin ventilation and combustion-supporting air inlet expansion joint, and the cabin ventilation and air exhaust component is arranged at the upper part of the rear end of the engine room component. By adopting the structure, the invention directly cools the gas turbine by the ventilation air flowing through the gas turbine cabin, and then discharges and radiates heat by the cabin ventilation exhaust component, so that the arrangement of a cooling device can be reduced, the manufacturing cost is reduced, and the air is adopted as the coolant, so that the gas turbine is convenient to obtain and low in use cost.

Description

Cabin ventilation system suitable for aero-retrofit gas turbine and aero-retrofit gas turbine

Technical Field

The invention relates to the technical field of aero-modified gas turbine equipment, in particular to a cabin ventilation system suitable for an aero-modified gas turbine and the aero-modified gas turbine.

Background

Aero-retrofit gas turbine generator sets are widely used in the field of distributed energy power generation due to their flexible configuration, compact profile and low maintenance characteristics.

The core components of aero-retrofit gas turbines are derived from aero engines. When the aeroengine works, air is compressed by the air compressor, enters the combustion chamber, is mixed with chemical fuel and combusted to generate a large amount of high-temperature and high-pressure gas, and then is expanded by the turbine and the spray pipe, and the expanded gas is discharged from the tail nozzle at a high speed and is mixed with the gas of the outer duct to act together, so that the aircraft is pushed to fly at a high speed.

The heat dissipation problem of the aero-modified gas turbine using the aero-engine as a core component is particularly remarkable because the working characteristic of the aero-engine is that the thrust of the engine is obtained by heating air and expanding work, but no cabin ventilation system specially used for the aero-modified gas turbine exists in the domestic market at present, so that the special design of the cabin ventilation system for the aero-modified gas turbine is particularly important.

Disclosure of Invention

In view of the drawbacks of the prior art, it is an object of the present invention to provide a cabin ventilation system for a aero-retrofit gas turbine and an aero-retrofit gas turbine.

The cabin ventilation system suitable for the aero-retrofit gas turbine comprises an air inlet filter chamber assembly, a cabin ventilation and combustion-supporting air inlet chamber, a cabin ventilation and combustion-supporting air inlet expansion joint, a combustion cabin chamber assembly and a cabin ventilation exhaust assembly, wherein the cabin ventilation and combustion-supporting air inlet expansion joint is arranged on the cabin ventilation and combustion-supporting air inlet chamber;

the air inlet filter chamber component passes through the cabin ventilation and combustion-supporting air inlet chamber and is connected with the combustion engine cabin component through a plurality of pipelines, the cabin ventilation and combustion-supporting air inlet chamber is connected with the combustion engine cabin component through the cabin ventilation and combustion-supporting air inlet expansion joint, and the cabin ventilation and air exhaust component is arranged at the upper part of the rear end of the combustion engine cabin component.

In some embodiments, the plurality of pipelines comprise a pipeline I and a pipeline II, wherein a cabin ventilation expansion joint and a cabin ventilation air inlet air brake are arranged on the pipeline I, a branch is also arranged on the pipeline I, and the cabin ventilation expansion joint and the cabin ventilation air inlet air brake are also arranged on the branch;

the cabin ventilation expansion joint on the pipeline I and the cabin ventilation expansion joint on the branch are arranged oppositely, and the cabin ventilation air inlet damper on the pipeline I and the cabin ventilation air inlet damper on the branch are arranged oppositely;

a combustion-supporting air inlet expansion joint and a combustion-supporting air inlet silencer are arranged on the second pipeline;

air enters the air inlet filter chamber assembly and is divided into two paths by the air inlet of the air inlet channel of the combustion engine and the air inlet partition plate of the engine room after being subjected to the primary rough filtration and the secondary fine filtration;

one path passes through the cabin ventilation expansion joint and the cabin ventilation air inlet air gate, passes through the cabin ventilation and combustion-supporting air inlet chamber and enters the upper combustion engine room air inlet channel of the combustion engine room assembly;

the other path passes through the combustion-supporting air inlet expansion joint and the combustion-supporting air inlet silencer, passes through the cabin ventilation and combustion-supporting air inlet chamber and enters the upper combustion cabin air inlet channel of the combustion cabin assembly.

In some embodiments, the combustion engine compartment assembly comprises a compartment temperature sensor, a compartment pressure sensor and a combustion engine compartment, wherein the compartment temperature sensor and the compartment pressure sensor are connected to the combustion engine compartment, and the combustion engine is arranged in the combustion engine compartment.

In some embodiments, the air inlet filter chamber assembly comprises an air inlet filter rain cover and an air inlet filter chamber, wherein the air inlet filter rain cover is arranged at one side outside the air inlet filter chamber, and a first-stage rough filter, a heating coil and a second-stage fine filter are arranged in the air inlet filter chamber;

and the air inlet filtering rain cover, the first-stage rough filtering, the heating coil and the second-stage fine filtering are sequentially arranged on the same side of the air inlet filtering chamber component.

In some embodiments, a gas inlet channel gas inlet and a gas cabin gas inlet partition plate are further arranged in the gas inlet filter chamber, and the gas inlet filter chamber is divided into a gas inlet channel gas inlet chamber and a gas cabin gas inlet chamber by the gas inlet channel gas inlet and the gas cabin gas inlet partition plate.

In some embodiments, an ambient temperature sensor is further disposed on the outdoor side of the air intake filtering enclosure, and the ambient temperature sensor is disposed on the air intake filtering enclosure;

the other side outside the air inlet filter chamber is also provided with a fuel engine air inlet chamber pressure difference sensor and a fuel engine room air inlet chamber pressure difference sensor, the fuel engine air inlet chamber pressure difference sensor is connected with the fuel engine air inlet chamber, and the fuel engine room air inlet chamber pressure difference sensor is connected with the fuel engine room air inlet chamber.

In some embodiments, the first stage coarse filtration, the heating coil, and the second stage fine filtration are all vertically disposed in the intake filter chamber, and the gas inlet of the gas turbine and the gas inlet separator of the gas turbine chamber are laterally disposed in the intake filter chamber.

In some embodiments, the cabin ventilation exhaust assembly comprises a cabin ventilation exhaust damper connection section, a cabin ventilation exhaust damper, a cabin ventilation exhaust blower motor, a cabin ventilation exhaust muffler, and a cabin ventilation exhaust rain shield;

the cabin ventilation exhaust air brake connecting section is connected with the cabin ventilation exhaust air brake, the cabin ventilation exhaust air brake is connected with the cabin ventilation exhaust fan, the cabin ventilation exhaust fan is connected with the cabin ventilation exhaust silencer, the cabin ventilation exhaust silencer is connected with the cabin ventilation exhaust rain cover, and one side of the cabin ventilation exhaust fan is connected with the cabin ventilation exhaust fan motor;

and the cabin ventilation exhaust air brake, the cabin ventilation exhaust fan motor, the cabin ventilation exhaust silencer and the cabin ventilation exhaust rain cover are symmetrically arranged in pairs.

In some embodiments, the on/off of the cabin ventilation exhaust assembly and the flow rate of ventilation are related to the signaling of the cabin temperature sensor and the cabin pressure sensor.

An aero-retrofit gas turbine comprising a cabin ventilation system as described above adapted for an aero-retrofit gas turbine.

Compared with the prior art, the invention has the following beneficial effects:

the invention is characterized in that an air inlet filter chamber component, a cabin ventilation and combustion-supporting air inlet chamber, a cabin ventilation and combustion-supporting air inlet expansion joint, a combustion cabin chamber component and a cabin ventilation and exhaust component are arranged, wherein the air inlet filter chamber component passes through the cabin ventilation and combustion-supporting air inlet chamber through a plurality of pipelines and is communicated with the combustion cabin chamber component, the cabin ventilation and combustion-supporting air inlet chamber is connected with the combustion cabin chamber component through the cabin ventilation and combustion-supporting air inlet expansion joint, and the cabin ventilation and exhaust component is arranged at the upper part of the rear end of the combustion cabin chamber component;

by adopting the structure, the ventilation air and the combustion air share the set of air inlet filter chamber components, so that the combustion-supporting and heat-dissipating ventilation effects of the gas engine can be achieved at the same time, other air filter systems are not needed to be additionally arranged, the manufacturing cost is reduced, the application is convenient, and the working efficiency is greatly improved;

through adopting above-mentioned structure, directly will flow through the ventilation air in combustion engine cabin and cool off the combustion engine, the rethread cabin ventilation exhaust subassembly discharges the heat dissipation, can reduce cooling device's arrangement, reduces manufacturing cost, and adopts air as the coolant, acquires conveniently, use cost is low.

Drawings

Other features, objects and advantages of the present invention will become more apparent upon reading of the detailed description of non-limiting embodiments, given with reference to the accompanying drawings in which:

FIG. 1 is a schematic view of a cabin ventilation system of the present invention adapted for use with an aeroderivative gas turbine;

FIG. 2 is a schematic illustration of the inlet filter house assembly of the cabin ventilation system of the aero-retrofit gas turbine of the present invention;

FIG. 3 is a schematic view of the cabin ventilation exhaust assembly of the cabin ventilation system of the present invention adapted for use with an aeroderivative gas turbine.

Reference numerals:

gas inlet filter chamber assembly 1 gas turbine compartment 403

Inlet air filtering rain cover 101 gas turbine 4031

First stage prefilter 102 cabin ventilation exhaust assembly 5

Heating coil 103 cabin ventilation exhaust damper connection section 501

Second stage fine filtration 104 cabin ventilation exhaust damper 502

Cabin ventilation and exhaust fan 503 for intake air of gas inlet of combustion engine and intake partition 105 of combustion engine cabin

Ambient temperature sensor 106 cabin ventilation exhaust fan motor 504

Cabin ventilation exhaust silencer 505 of gas turbine inlet chamber pressure difference sensor 107

Cabin ventilation and exhaust rain cover 506 of combustion engine cabin intake chamber differential pressure sensor 108

Cabin ventilation expansion joint 6 of air inlet filter chamber 109

Cabin ventilation and air intake damper 7 of air inlet chamber 1091 of gas turbine inlet

Combustion-supporting intake expansion joint 8 of engine room intake chamber 1092

Combustion-supporting air intake silencer 9 of cabin ventilation and combustion-supporting air inlet chamber 2

Cabin ventilation and combustion-supporting air inlet expansion joint 3 pipeline one 10

Combustion engine room assembly 4 branch 1001

Cabin temperature sensor 401 pipeline two 11

Cabin pressure sensor 402

Detailed Description

The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the present invention, but are not intended to limit the invention in any way. It should be noted that variations and modifications could be made by those skilled in the art without departing from the inventive concept. These are all within the scope of the present invention.

As shown in fig. 1-3, the cabin ventilation system of the present invention suitable for aeroderivative gas turbines comprises an intake filter chamber assembly 1, a cabin ventilation and combustion air intake chamber 2, a cabin ventilation and combustion air intake expansion joint 3, a combustion cabin chamber assembly 4 and a cabin ventilation exhaust assembly 5. The air intake filter chamber assembly 1 passes through the cabin ventilation and combustion-supporting air intake chamber 2 through a plurality of pipelines and is connected with the combustion engine cabin assembly 4, the cabin ventilation and combustion-supporting air intake chamber 2 is connected with the combustion engine cabin assembly 4 through the cabin ventilation and combustion-supporting air intake expansion joint 3, and the cabin ventilation and exhaust assembly 5 is arranged at the upper part of the rear end of the combustion engine cabin assembly 4.

The pipelines comprise a pipeline I10 and a pipeline II 11, the pipeline I10 is provided with a cabin ventilation expansion joint 6 and a cabin ventilation air inlet air brake 7, the pipeline I10 is also provided with a branch 1001, and the branch 1001 is also provided with the cabin ventilation expansion joint 6 and the cabin ventilation air inlet air brake 7. The cabin ventilation expansion joint 6 on the first pipeline 10 and the cabin ventilation expansion joint 6 on the branch 1001 are oppositely arranged, and the cabin ventilation air inlet damper 7 on the first pipeline 10 and the cabin ventilation air inlet damper 7 on the branch 1001 are oppositely arranged. The second pipeline 11 is provided with a combustion-supporting air inlet expansion joint 8 and a combustion-supporting air inlet silencer 9. The cabin assembly 4 includes a cabin temperature sensor 401, a cabin pressure sensor 402, and a cabin 403, the cabin temperature sensor 401 and the cabin pressure sensor 402 are connected to the cabin 403, and a combustion engine 4031 is disposed in the cabin 403.

The air inlet filter chamber assembly 1 comprises an air inlet filter rain cover 101 and an air inlet filter chamber 109, wherein the air inlet filter rain cover 101 is arranged on one side outside the air inlet filter chamber 109, and a first-stage rough filter 102, a heating coil 103 and a second-stage fine filter 104 are arranged in the air inlet filter chamber 109. The inlet air filtering rain cover 101, the first-stage rough filter 102, the heating coil 103 and the second-stage fine filter 104 are sequentially arranged on the same side of the inlet air filtering chamber assembly 1. The gas inlet filter chamber 109 is further provided with a gas inlet and a gas inlet partition plate 105 for a gas engine room, and the gas inlet filter chamber 109 is divided into a gas inlet and a gas inlet 1091 and a gas inlet 1092 for the gas engine room by the gas inlet and the gas inlet partition plate 105 for the gas engine room. An ambient temperature sensor 106 is further arranged on the outer side of the air inlet filter chamber 109, and the ambient temperature sensor 106 is arranged on the air inlet filter rain cover 101. The other side outside the air intake filtering chamber 109 is further provided with a fuel engine air intake chamber pressure difference sensor 107 and a fuel engine room air intake chamber pressure difference sensor 108, and the fuel engine air intake chamber pressure difference sensor 107 is connected to the fuel engine air intake chamber 1091, and the fuel engine room air intake chamber pressure difference sensor 108 is connected to the fuel engine room air intake chamber 1092. The first coarse filter 102, the heating coil 103 and the second fine filter 104 are vertically arranged in an air inlet filter chamber 109, and an air inlet of a gas engine inlet and an air inlet partition 105 of a gas engine room are transversely arranged in the air inlet filter chamber 109.

The cabin ventilation exhaust assembly 5 comprises a cabin ventilation exhaust damper connection section 501, a cabin ventilation exhaust damper 502, a cabin ventilation exhaust blower 503, a cabin ventilation exhaust blower motor 504, a cabin ventilation exhaust muffler 505, and a cabin ventilation exhaust weather hood 506. The cabin ventilation exhaust damper connecting section 501 is connected with a cabin ventilation exhaust damper 502, the cabin ventilation exhaust damper 502 is connected with a cabin ventilation exhaust fan 503, the cabin ventilation exhaust fan 503 is connected with a cabin ventilation exhaust silencer 505, the cabin ventilation exhaust silencer 505 is connected with a cabin ventilation exhaust rain cover 506, and one side of the cabin ventilation exhaust fan 503 is connected with a cabin ventilation exhaust fan motor 504. The cabin ventilation exhaust damper 502, the cabin ventilation exhaust blower 503, the cabin ventilation exhaust blower motor 504, the cabin ventilation exhaust muffler 505, and the cabin ventilation exhaust weather hood 506 are all symmetrically disposed in pairs.

In particular, in the present embodiment, the rain cover 101 ensures that the inlet filter house assembly 1 can operate in severe weather conditions.

Specifically, in the present embodiment, clean air is used for mixed chemical fuel combustion and cabin ventilation cooling, respectively, after the outside air is filtered through the inlet filter house assembly 1.

Specifically, in this embodiment, the filtering grade of the first stage of coarse filtration 102 should conform to the G4 grade conforming to EN 779. The second stage of fine filtration 104 should have a filtration rating that meets the F9 rating of EN 779.

Specifically, in this embodiment, the heating coil 103 should be turned on when the ambient temperature is less than 4 degrees celsius, as controlled by the ambient temperature sensor 106.

Specifically, in the present embodiment, the air entering the intake filtering chamber 109 is filtered for impurities by the first-stage coarse filtration 102 and the second-stage fine filtration 104, and the filtered air is separated into ventilation air and combustion air by the engine intake duct intake and engine room intake partition 105, which are stored in the engine intake duct intake 1091 and the engine room intake 1092, respectively.

Specifically, in the present embodiment, the flow of ventilation air into the engine compartment 403 is monitored by the engine inlet chamber pressure differential sensor 108, and an alarm is triggered when the air pressure differential is higher than 1"wg (2.5 mm).

Specifically, in the present embodiment, the flow of combustion air into the combustion chamber 403 is monitored by the combustion chamber inlet chamber differential pressure sensor 107, and when the differential pressure reaches 5"wg (127 mm), the chamber ventilation inlet damper 602 is simultaneously opened, and when the differential pressure reaches 8" wg (203 mm), the shutdown of the whole unit is triggered.

Specifically, in the present embodiment, the ventilation air filtered in the intake filter chamber 109 is communicated with the cabin ventilation and combustion-supporting intake chamber 2 through the cabin ventilation expansion joint 6 and the cabin ventilation intake damper 7 in cooperation with the first pipe 10 and the branch 1001.

Specifically, in the present embodiment, the combustion air filtered in the intake filtering chamber 109 is communicated with the cabin ventilation and combustion air intake chamber 2 through the combustion air intake expansion joint 8 and the combustion air intake silencer 9 in cooperation with the second pipeline 11.

Specifically, in the present embodiment, ventilation air in the upper combustion chamber 403 of the combustion chamber assembly 4 is discharged via the chamber ventilation exhaust assembly 5 connected to the combustion chamber 403.

Specifically, in this embodiment, 2 cabin ventilation exhaust dampers 502 on the cabin ventilation exhaust assembly 5 may be selectively opened singly or all of them for exhausting.

Specifically, in the present embodiment, the flow rate of the ventilation air in the combustion chamber 403 is determined by the rotational speed of the cabin ventilation exhaust fans 503 controlled by the cabin ventilation exhaust fan motor on both sides.

Specifically, in the present embodiment, the ventilation air in the combustion chamber 403 is discharged through the cabin ventilation exhaust muffler 505, ensuring that the noise at the time of discharge is less than 85dB.

Specifically, in the present embodiment, the cabin ventilation exhaust rain cover 506 is provided to ensure that the gas turbine 4031 can operate in any weather condition.

Specifically, in the present embodiment, the on/off of the cabin ventilation exhaust assembly 5 and the flow rate of ventilation are related to the signaling of the cabin temperature sensor 401 and the cabin pressure sensor 402.

The foregoing is a basic embodiment of the present invention, and a technical solution of the present invention is further described in detail below by means of a preferred embodiment;

example 1

As shown in fig. 1 to 3, the intake filtering rain cover 101 of the cabin ventilation system of the aero-retrofit gas turbine provided on the intake filtering chamber assembly 1 can prevent external rainwater from entering, and the entering air can be filtered through the first stage rough filter 102 and the second stage fine filter 104 to obtain ventilation air and combustion air meeting requirements. When the ambient temperature is lower than 4 ℃, the ambient temperature sensor 106 sends out a signal instruction to control the heating coil 103 to be started for heating, so that the air inlet filter chamber assembly 1 is prevented from icing. The air entering the inlet filter house assembly 1 is split into two paths of air by the engine inlet and engine compartment intake partition 105. One path of air: cabin ventilation air communicates with the cabin ventilation and combustion air intake chamber 2 through the cabin ventilation expansion joint 6 and the cabin ventilation air intake damper 7 in cooperation with the first conduit 10 and the branch 1001. The other path of air: the combustion air is communicated with the cabin ventilation and combustion-supporting air inlet chamber 2 through the combustion-supporting air inlet expansion joint 8 and the combustion-supporting air inlet silencer 9 and matched with the pipeline II 11. The flow control of the two-way air is controlled by the engine intake chamber differential pressure sensor 107 and the engine room intake chamber differential pressure sensor 108. When the engine intake chamber differential pressure sensor 107 shows that the air pressure difference is higher than 1"wg (2.5 mm), an alarm is triggered. When the differential pressure sensor 108 of the air inlet chamber of the engine room displays that the air pressure difference reaches 5 'Wg (127 mm), the ventilation inlet air brake 7 of the engine room is simultaneously opened, and when the pressure difference reaches 8' Wg (203 mm), the shutdown of the whole unit is triggered.

The cabin ventilation and combustion air intake chamber 2 is connected with the combustion cabin chamber assembly 4 through a cabin ventilation and combustion air intake expansion joint 3. The ventilation air flowing through the combustion chamber 403 is exhausted through a chamber ventilation exhaust assembly 5 disposed over the rear of the combustion chamber assembly 4. The cabin ventilation exhaust assembly 5 is connected to the combustion cabin assembly 4 by a cabin ventilation exhaust damper connection 501, and two cabin ventilation exhaust fans 503 on the cabin ventilation exhaust assembly 5 are controlled by two cabin ventilation exhaust fan motors 504. When the cabin temperature sensor 401 senses that the temperature in the combustion cabin 403 reaches 60 degrees celsius, both cabin ventilation exhaust blower motors 504 in the cabin ventilation exhaust assembly 5 are turned on, and all of the cabin ventilation exhaust dampers 502 and the cabin ventilation exhaust blower 503 are turned on. When the cabin temperature sensor 401 senses that the temperature in the combustion cabin 403 reaches 66 degrees celsius, the whole unit is shut down for cooling. The cabin pressure sensor 402 may monitor the negative pressure level in the combustion cabin 403 and may trigger an alarm when the internal and external air pressure differential is higher than-1 "wg (-2.5 mm). The ventilation air in the cabin 403 can be silenced and exhausted through the cabin ventilation exhaust muffler 505, ensuring that the noise at the exhaust is less than 85dB. The cabin ventilation exhaust rain hood 506 ensures that the cabin ventilation exhaust assembly 5 remains operational in the event of a harsh environment.

Example 2

A aero-retrofit gas turbine comprising the cabin ventilation system of embodiment 1 adapted for an aero-retrofit gas turbine.

In the description of the present application, it should be understood that the terms "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like indicate orientations or positional relationships based on the orientations or positional relationships illustrated in the drawings, merely to facilitate description of the present application and simplify the description, and do not indicate or imply that the devices or elements being referred to must have a specific orientation, be configured and operated in a specific orientation, and are not to be construed as limiting the present application.

The foregoing describes specific embodiments of the present invention. It is to be understood that the invention is not limited to the particular embodiments described above, and that various changes or modifications may be made by those skilled in the art within the scope of the appended claims without affecting the spirit of the invention. The embodiments of the present application and features in the embodiments may be combined with each other arbitrarily without conflict.

Claims (9)

1. A cabin ventilation system suitable for aero-retrofit gas turbines, characterized by comprising an air intake filter chamber assembly (1), a cabin ventilation and combustion-supporting air intake chamber (2), a cabin ventilation and combustion-supporting air intake expansion joint (3), a combustion cabin chamber assembly (4) and a cabin ventilation exhaust assembly (5);

the air inlet filter chamber assembly (1) penetrates through the cabin ventilation and combustion-supporting air inlet chamber (2) through a plurality of pipelines and is connected with the cabin chamber assembly (4), the cabin ventilation and combustion-supporting air inlet chamber (2) is connected with the cabin chamber assembly (4) through the cabin ventilation and combustion-supporting air inlet expansion joint (3), and the cabin ventilation and air exhaust assembly (5) is arranged on the cabin chamber assembly (4).

2. Cabin ventilation system suitable for aeroderivative gas turbines according to claim 1, wherein a plurality of said lines comprises a first line (10) and a second line (11), said first line (10) being provided with a cabin ventilation expansion joint (6) and a cabin ventilation inlet damper (7), and said first line (10) being further provided with a branch (1001), said branch (1001) being also provided with said cabin ventilation expansion joint (6) and said cabin ventilation inlet damper (7);

the cabin ventilation expansion joint (6) on the pipeline I (10) and the cabin ventilation expansion joint (6) on the branch (1001) are arranged oppositely, and the cabin ventilation air inlet air brake (7) on the pipeline I (10) and the cabin ventilation air inlet air brake (7) on the branch (1001) are arranged oppositely;

and a combustion-supporting air inlet expansion joint (8) and a combustion-supporting air inlet silencer (9) are arranged on the second pipeline (11).

3. Cabin ventilation system for an aeroderivative gas turbine according to claim 2, wherein the combustion chamber assembly (4) comprises a cabin temperature sensor (401), a cabin pressure sensor (402) and a combustion chamber (403), wherein the combustion chamber (403) is connected to the cabin temperature sensor (401) and the cabin pressure sensor (402), and wherein a combustion engine (4031) is arranged in the combustion chamber (403).

4. Cabin ventilation system suitable for aero-retrofit gas turbines according to claim 1, characterized in that said inlet air filter chamber assembly (1) comprises an inlet air filter rain cover (101) and an inlet air filter chamber (109), said inlet air filter rain cover (101) being arranged on the outer side of said inlet air filter chamber (109), and said inlet air filter chamber (109) being provided with a first stage of coarse filtration (102), a heating coil (103) and a second stage of fine filtration (104);

and the air inlet filtering rain cover (101), the first-stage rough filter (102), the heating coil (103) and the second-stage fine filter (104) are sequentially arranged on the same side of the air inlet filtering chamber assembly (1) from outside to inside.

5. Cabin ventilation system for an aero-retrofit gas turbine according to claim 4, characterized in that a gas inlet and a gas cabin inlet partition (105) are also provided in the inlet filter chamber (109), the interior of the inlet filter chamber (109) being divided into a gas inlet (1091) and a gas cabin inlet (1092) by the gas inlet and gas cabin inlet partition (105).

6. Cabin ventilation system for aero-retrofit gas turbines according to claim 5, characterized in that an ambient temperature sensor (106) is further provided on the outer side of the inlet filter chamber (109), said ambient temperature sensor (106) being provided on the inlet filter rain cover (101);

the other side outside the air inlet filter chamber (109) is further provided with a fuel engine air inlet chamber pressure difference sensor (107) and a fuel engine room air inlet chamber pressure difference sensor (108), the fuel engine air inlet chamber pressure difference sensor (107) is connected to the fuel engine air inlet chamber (1091), and the fuel engine room air inlet chamber pressure difference sensor (108) is connected to the fuel engine room air inlet chamber (1092).

7. Cabin ventilation system for aero-retrofit gas turbines according to claim 6, wherein said first stage coarse filtration (102), said heating coil (103) and said second stage fine filtration (104) are all vertically arranged within said inlet filter chamber (109), said gas inlet and gas cabin inlet partition (105) being laterally arranged within said inlet filter chamber (109).

8. Cabin ventilation system suitable for aeroderivative gas turbines according to claim 1, wherein the cabin ventilation exhaust assembly (5) comprises a cabin ventilation exhaust damper connection section (501), a cabin ventilation exhaust damper (502), a cabin ventilation exhaust fan (503), a cabin ventilation exhaust fan motor (504), a cabin ventilation exhaust muffler (505) and a cabin ventilation exhaust rain cover (506);

the cabin ventilation exhaust air brake connecting section (501) is connected with the cabin ventilation exhaust air brake (502), the cabin ventilation exhaust air brake (502) is connected with the cabin ventilation exhaust air fan (503), the cabin ventilation exhaust air fan (503) is connected with the cabin ventilation exhaust silencer (505), the cabin ventilation exhaust silencer (505) is connected with the cabin ventilation exhaust rain cover (506), and one side of the cabin ventilation exhaust air fan (503) is connected with the cabin ventilation exhaust air fan motor (504);

and the cabin ventilation exhaust air brake (502), the cabin ventilation exhaust fan (503), the cabin ventilation exhaust fan motor (504), the cabin ventilation exhaust silencer (505) and the cabin ventilation exhaust rain cover (506) are symmetrically arranged in pairs.

9. Aeroderivative gas turbine, comprising a cabin ventilation system according to any one of claims 1-8, suitable for aeroderivative gas turbines.