CN214190132U - Turbine engine cabin ventilation cooling device - Google Patents
Turbine engine cabin ventilation cooling device Download PDFInfo
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- CN214190132U CN214190132U CN202022664442.XU CN202022664442U CN214190132U CN 214190132 U CN214190132 U CN 214190132U CN 202022664442 U CN202022664442 U CN 202022664442U CN 214190132 U CN214190132 U CN 214190132U
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- exhaust pipe
- turbine engine
- cooling device
- engine compartment
- engine
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Abstract
The utility model relates to a turbine engine cabin ventilation cooling device, which comprises an air door (1), an electric mechanism (2), a front shutter (3), a rear shutter (4), an outer exhaust pipe (5), an inner exhaust pipe (6), an exhaust baffle (8), a turbine engine (9) and an engine cabin (11); in the working process of the turbine engine, the surface temperature of the exhaust pipe can be reduced through the ejection effect generated by the working of the turbine engine. Through the design of the exhaust baffle, the high-temperature exhaust of the turbine engine is prevented from flowing back to enter an engine compartment, and the normal work of the turbine engine is ensured; the design structure is simple and the weight is light.
Description
Technical Field
The utility model belongs to aircraft structural design field relates to a turbine engine cabin ventilation cooling device, especially can improve turbine engine under-deck cooling air distribution, prevent the exhaust problem of backflowing, reduces outer exhaust pipe surface temperature.
Background
The turbine engine that uses on present seaplane installs in fuselage wing radome fairing, because turbine engine body structural style limits, can't design special intake duct, restricts to the restriction in installation space simultaneously, and the blast pipe can't be designed into straight appearance, and turbine engine work in the suction effect of compressor forms the negative pressure in engine air inlet department, with turbine engine exhaust suck-back get into the engine compartment, leads to the engine compartment in high temperature and turbine engine work unusual.
The fireproof partition plate and the exhaust baffle are additionally arranged in the turbine engine cabin, so that air inlet and exhaust of the turbine engine are isolated, the problem of exhaust backflow is solved, the ejection holes are additionally formed in the outer exhaust pipe, and ejection effect is generated by high-speed airflow generated by the operation of the turbine engine to cool the surface temperature of the outer exhaust pipe.
At present, no relevant technical disclosure is found in the prior art.
SUMMERY OF THE UTILITY MODEL
The utility model aims at: the ventilating and cooling device for the turbine engine cabin and the design method can prevent negative pressure generated at a working air inlet of the turbine engine from sucking working waste gas into the engine cabin, realize normal work of the turbine engine and reduce the surface temperature of an exhaust pipe.
In order to achieve the above purpose, the ventilation cooling device for the turbine engine compartment is installed in an engine compartment 11, and is characterized by comprising a ventilation door 1, an electric mechanism 2, a front louver 3, a rear louver 4, an outer exhaust pipe 5, an inner exhaust pipe 6, an exhaust baffle plate 8, a turbine engine 9 and the engine compartment 11;
a fireproof partition plate 115 is arranged in the engine compartment 11 to divide the engine compartment 11 into a front part and a rear part; the front part of the engine room 11 is provided with an air opening 111 and a front shutter window 112; the rear part is provided with a rear louver 113 and an outer air outlet 114;
the air door 1 is rotatably connected with an air opening 111 of the engine compartment 11 through the electric mechanism 2; the air door 1 is used for the work of a turbine engine and the ventilation and air intake of a cooling device;
the front louver 3 and the rear louver 4 are respectively and fixedly connected with the front louver 112 and the rear louver 113; the front louver 3 is used for improving the ventilation cooling effect of the turbine engine; the rear shutter 4 is used for ejecting air inlet through an exhaust pipe;
one end of the turbine engine 9, which is close to the air door 1, is provided with an air inlet 10, and the other end of the turbine engine is detachably connected with the inner exhaust pipe 6 through a fastening device; the inner exhaust duct 6 passes through a fire bulkhead 115 of the engine compartment 11; the outer exhaust pipe 5 and the inner exhaust pipe 6 are concentric and are sleeved on the inner exhaust pipe 6, an injection hole 7 is symmetrically formed in the center of the outer exhaust pipe 5, a gap exists between the exhaust pipe 5 and the inner exhaust pipe 6, one end of the outer exhaust pipe 5 is fixedly connected to the fireproof partition plate 115, and the other end of the outer exhaust pipe 5 is fixedly connected to an outer exhaust port 114 on the engine compartment 11; the injection hole 7 is formed in the outer exhaust pipe 5, and cooling air outside the engine can enter an annular cavity between the inner exhaust pipe and the outer exhaust pipe through the injection hole under the injection effect of exhaust of the outlet of the inner exhaust pipe 6 so as to cool the exhaust pipe, and then the cooling air is mixed with exhaust of the turbine engine and is exhausted outside the engine together to cool the surface temperature of the exhaust pipe;
the exhaust baffle 8 is of an annular structure with a flange, one end of the exhaust baffle is fixed on the outer circumference of the inner exhaust pipe 6, and the flange at the other end is provided with a rubber ring 81 which is attached and sealed with a fireproof clapboard 115 of the engine compartment 11. To prevent the negative pressure generated at the working air inlet of the turbine engine from drawing the working exhaust gases into the engine compartment.
In a possible embodiment, a gap exists between the exhaust pipe 5 and the inner exhaust pipe 6, and the gap value is the gap value which enables the injection effect to be optimal through CFD calculation and analysis.
In a possible embodiment, the outer exhaust pipe 5 is longer than the inner exhaust pipe 6, and the length difference between the outer exhaust pipe 5 and the inner exhaust pipe 6 is the length difference which enables the injection effect to be optimal through CFD calculation and analysis.
In one possible embodiment, the rubber ring 81 is a fire-resistant rubber. So as to realize long-term high-temperature resistant work without failure.
In one possible embodiment, the fire-retardant rubber may be selected from one of silicone rubber and fluorosilicone rubber.
In a possible embodiment, the electric machine 2 needs to remain operating normally for a certain time after a fire in the engine compartment.
The utility model has the advantages that: the turbine engine compartment ventilation cooling device is provided, and the surface temperature of an exhaust pipe can be reduced through the injection effect generated by the operation of the turbine engine in the operation process of the turbine engine. Through the design of the exhaust baffle, the high-temperature exhaust of the turbine engine is prevented from flowing back to enter an engine compartment, and the normal work of the turbine engine is ensured; the design structure is simple and the weight is light.
An exhaust baffle is adopted to isolate an annular cavity between the engine compartment and the outer exhaust pipe. The exhaust baffle prevents the high temperature exhaust gas of the turbine engine from flowing back into the engine compartment through the annular cavity. The normal work of the turbine engine is ensured.
Analyzing the influence of the gap and the length of the inner exhaust pipe and the outer exhaust pipe on the injection effect by adopting a CFD analysis method according to the installation position on the machine; and analyzing the influence of the position of the air door and the position of the shutter on the air flow distribution.
Drawings
FIG. 1 is a schematic structural view of an exhaust damper device of a turbine engine according to the present invention
FIG. 2 is a schematic diagram of the engine compartment of the present invention
In the figure, 1, a damper, 2, an electric mechanism, 3, a shutter, 5, an outer exhaust pipe, 6, an inner exhaust pipe, 7, an injection hole, 8, an exhaust baffle, 9, a turbine engine, 10, an air inlet of the turbine engine, 11 and an engine compartment are arranged.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings and embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, other embodiments obtained by a person of ordinary skill in the art without creative work all belong to the protection scope of the present invention.
A turbine engine cabin ventilation cooling device is arranged in an engine cabin 11 and is characterized by comprising a ventilation door 1, an electric mechanism 2, a front shutter 3, a rear shutter 4, an outer exhaust pipe 5, an inner exhaust pipe 6, an exhaust baffle 8, a turbine engine 10 and the engine cabin 11;
a fireproof partition plate 115 is arranged in the engine compartment 11 to divide the engine compartment 11 into a front part and a rear part; the front part of the engine room 11 is provided with an air opening 111 and a front shutter window 112; the rear part is provided with a rear louver 113 and an outer air outlet 114;
the air door 1 is rotatably connected with an air opening 111 of the engine compartment 11 through the electric mechanism 2; the air door 1 is used for the work of a turbine engine and the ventilation and air intake of a cooling device;
the front louver 3 and the rear louver 4 are respectively and fixedly connected with the front louver 112 and the rear louver 113; the front louver 3 is used for improving the ventilation cooling effect of the turbine engine; the rear shutter 4 is used for ejecting air inlet through an exhaust pipe;
one end of the turbine engine 9, which is close to the air door 1, is provided with an air inlet 10, and the other end of the turbine engine is detachably connected with the inner exhaust pipe 6 through a fastening device; the inner exhaust duct 6 passes through a fire bulkhead 115 of the engine compartment 11; the outer exhaust pipe 5 and the inner exhaust pipe 6 are concentric and are sleeved on the inner exhaust pipe 6, an injection hole 7 is symmetrically formed in the center of the outer exhaust pipe 5, a gap exists between the exhaust pipe 5 and the inner exhaust pipe 6, one end of the outer exhaust pipe 5 is fixedly connected to the fireproof partition plate 115, and the other end of the outer exhaust pipe 5 is fixedly connected to an outer exhaust port 114 on the engine compartment 11;
the exhaust baffle 8 is of an annular structure with a flange, one end of the exhaust baffle is fixed on the outer circumference of the inner exhaust pipe 6, and the flange at the other end is provided with a rubber ring 81 which is attached and sealed with a fireproof clapboard 115 of the engine compartment 11. To prevent the negative pressure generated at the working air inlet of the turbine engine from sucking the working exhaust gases into the engine compartment;
a gap exists between the exhaust pipe 5 and the inner exhaust pipe 6, and the gap value is the gap value which enables the injection effect to be optimal through CFD calculation and analysis;
the outer exhaust pipe 5 is longer than the inner exhaust pipe 6, and the length difference between the outer exhaust pipe 5 and the inner exhaust pipe 6 is the length difference which enables the injection effect to be optimal through CFD calculation and analysis;
the rubber ring 81 is made of fireproof rubber. So as to realize long-term high-temperature resistant work without failure;
the fireproof rubber can be selected from silicon rubber;
the electric machine 2 needs to be kept in normal operation for a certain time after the engine compartment is on fire.
The above-mentioned embodiments only represent the preferred embodiments of the present invention, and the description thereof is more specific and detailed, but not to be construed as limiting the scope of the present invention. It should be noted that, for those skilled in the art, various changes and modifications can be made without departing from the spirit of the present invention, and these changes and modifications are all within the scope of the present invention. Therefore, the protection scope of the present invention should be subject to the appended claims.
Claims (6)
1. A turbine engine cabin ventilation cooling device is arranged in an engine cabin (11), and is characterized by comprising a ventilation door (1), an electric mechanism (2), a front shutter (3), a rear shutter (4), an outer exhaust pipe (5), an inner exhaust pipe (6), an exhaust baffle (8), a turbine engine (9) and the engine cabin (11);
a fireproof clapboard (115) is arranged in the engine compartment (11) and divides the engine compartment (11) into a front part and a rear part; the front part of the engine compartment (11) is provided with an air opening (111) and a front shutter window (112); the rear part is provided with a rear louver (113) and an outer exhaust port (114);
the air door (1) is rotatably connected with an air opening (111) of the engine room (11) through the electric mechanism (2); the air door (1) is used for ventilating and air inlet of a turbine engine working and cooling device;
the front louver (3) and the rear louver (4) are respectively and fixedly connected with the front louver window (112) and the rear louver window (113); the front shutter (3) is used for improving the ventilation cooling effect of the turbine engine; the rear shutter (4) is used for ejecting air inlet by an exhaust pipe;
one end of the turbine engine (9), which is close to the air door (1), is provided with an air inlet (10), and the other end of the turbine engine is detachably connected with the inner exhaust pipe (6) through a fastening device; the inner exhaust pipe (6) passes through a fire bulkhead (115) of the engine compartment (11); the outer exhaust pipe (5) and the inner exhaust pipe (6) are concentric and sleeved on the inner exhaust pipe (6), an injection hole (7) is symmetrically formed in the center of the outer exhaust pipe (5), a gap is formed between the outer exhaust pipe (5) and the inner exhaust pipe (6), one end of the outer exhaust pipe (5) is fixedly connected to the fireproof partition plate (115), and the other end of the outer exhaust pipe is fixedly connected with an outer exhaust port (114) in the engine compartment (11);
the exhaust baffle (8) is of an annular structure with a flanging, one end of the exhaust baffle is fixed on the outer circumference of the inner exhaust pipe (6), and the flanging at the other end of the exhaust baffle is provided with a rubber ring (81) which is attached and sealed with a fireproof partition plate (115) of the engine compartment (11).
2. The nacelle ventilation cooling device according to claim 1, wherein a gap exists between the exhaust pipe (5) and the inner exhaust pipe (6), and the gap value is a gap value that optimizes ejector effect through CFD calculation and analysis.
3. The nacelle ventilation cooling device according to claim 1, wherein the outer exhaust duct (5) is longer than the inner exhaust duct (6), and the difference in length between the outer exhaust duct (5) and the inner exhaust duct (6) is calculated and analyzed by CFD to optimize the ejector effect.
4. The turbine engine compartment ventilation cooling device of claim 1, wherein the rubber ring (81) is made of fireproof rubber so as to achieve long-term high temperature resistance without failure.
5. The turbine engine compartment air cooling device of claim 4, wherein the fire-resistant rubber is selected from one of silicone rubber and fluorosilicone rubber.
6. Turbine engine compartment ventilation cooling device according to claim 1, characterised in that said electric machine (2) is required to remain in normal operation for a certain time after a compartment fire.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022664442.XU CN214190132U (en) | 2020-11-17 | 2020-11-17 | Turbine engine cabin ventilation cooling device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022664442.XU CN214190132U (en) | 2020-11-17 | 2020-11-17 | Turbine engine cabin ventilation cooling device |
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| Publication Number | Publication Date |
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| CN214190132U true CN214190132U (en) | 2021-09-14 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202022664442.XU Active CN214190132U (en) | 2020-11-17 | 2020-11-17 | Turbine engine cabin ventilation cooling device |
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| CN (1) | CN214190132U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114687818A (en) * | 2022-04-14 | 2022-07-01 | 中国航发沈阳发动机研究所 | Exhaust device with front-rear injection structure |
-
2020
- 2020-11-17 CN CN202022664442.XU patent/CN214190132U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114687818A (en) * | 2022-04-14 | 2022-07-01 | 中国航发沈阳发动机研究所 | Exhaust device with front-rear injection structure |
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