CN105065136A - Mechanical equipment turbojet engine structure for chemical plant - Google Patents
Mechanical equipment turbojet engine structure for chemical plant Download PDFInfo
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- CN105065136A CN105065136A CN201510479911.1A CN201510479911A CN105065136A CN 105065136 A CN105065136 A CN 105065136A CN 201510479911 A CN201510479911 A CN 201510479911A CN 105065136 A CN105065136 A CN 105065136A
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Abstract
The invention provides a mechanical equipment turbojet engine structure for a chemical plant. The mechanical equipment turbojet engine structure comprises an air inlet, a shell, an outer duct, an inner duct, a combustion chamber, a low-pressure turbine, an air jet hole, a high-pressure turbine, a protection shell, a high-pressure compressor, a low-pressure compressor and a fan. One end of the shell is provided with the air inlet, and the shell is internally provided with the fan. The fan is arranged in the low-pressure compressor, and one end of the low-pressure compressor is connected with the low-pressure turbine. The low-pressure turbine is connected with the high-pressure turbine, and one end of the high-pressure turbine is connected with the high-pressure compressor. The combustion chamber is arranged between the low-pressure turbine and the high-pressure compressor. The mechanical equipment turbojet engine structure is compact in structure, capable of being stable in performance under long-time work and long in service life. A protection cover can protect the high-pressure turbine and the high-pressure compressor in the protection cover. The air jet hole can output internal burned gas in large displacement, the combustion chamber is complete in combustion, and utilization of raw materials is facilitated; and the mechanical equipment turbojet engine structure has good economic and social benefits and is suitable for being applied and popularized.
Description
Technical field
The present invention relates to a kind of turbojet engine, particularly a kind of chemical plant machinery turbojet architecture, belongs to mechanical equipment technical field.
Background technique
Turbojet engine application jet propulsion avoids rocket and the intrinsic weakness of athodyd.Because have employed turbo-driven gas compressor, so motor also has enough pressure to produce powerful thrust when low speed.Turbojet engine works according to " work cycle ".It is suck air from air, compressed and heating this process after, obtain the air of energy and momentum to discharge from propelling nozzle up to the speed of 2000 feet per second or about 1400 mph..When high speed jet stream ejection motor, drive gas compressor and turbine to continue to rotate simultaneously, maintain " work cycle ".The mechanical layout of turbogenerator is fairly simple, because it only comprises two main rotating parts, i.e. gas compressor and turbine, also has one or several firing chambers.But not all aspects of this motor all have this simplicity, because heating power and Aerodynamic Problems are more complicated.These problems are by firing chamber and the elevated operating temperature of turbine, the air-flow that constantly vary by gas compressor and turbine blade and discharge combustion gas and the design work forming the vent systems of propulsion jet stream causes.
At present some turbo machines come with some shortcomings part, and during work, heat can not shed in time; Secondary part trackslips relatively, and produce frictional heat, heat, as shed not in time, has a strong impact on its place of working reliability and working life; Therefore, for the problems referred to above, we have proposed a kind of chemical plant machinery turbojet architecture.
Summary of the invention
The technical problem to be solved in the present invention overcomes existing defect, provides a kind of chemical plant machinery turbojet architecture, engage smooth-going soft; Have suitable reserve capabillity, produce frictional heat, heat can shed in time, can not have a strong impact on its place of working reliability and working life; Effectively can solve the problem in background technique.
In order to solve the problems of the technologies described above, the invention provides following technological scheme: a kind of chemical plant machinery turbojet architecture, comprises suction port, shell, by-pass air duct, main duct, firing chamber, low-pressure turbine, puff prot, high pressure turbine, protecting crust, high-pressure compressor, low pressure compressor and fan; Described shell one end is provided with suction port and described enclosure is provided with fan; Described fan is installed on low compressor inside and described low compressor one end is connected with low-pressure turbine; Described low-pressure turbine is connected with high pressure turbine and high pressure turbine one end is connected with high-pressure compressor; Firing chamber is provided with between described low-pressure turbine and high-pressure compressor.
Further, described casing internal arranges by-pass air duct.
Further, described high pressure turbine and high-pressure compressor surface are provided with protecting crust.
Further, described protecting crust outer surface arranges main duct.
Further, described protecting crust one end is provided with puff prot.
The beneficial effect that compared with prior art the present invention reaches is:
Compact structure of the present invention, can in the lower stable performance that works long hours, and working life is of a specified duration, protective housing can protect high pressure turbine and the high-pressure compressor of its inside, puff prot can huge discharge output inside burning after gas, combustion chambers burn is abundant, is conducive to the utilization of raw material; There are good economic benefit and social effect, are applicable to promoting the use of.
Accompanying drawing explanation
Accompanying drawing is used to provide a further understanding of the present invention, and forms a part for specification, together with embodiments of the present invention for explaining the present invention, is not construed as limiting the invention.
In the accompanying drawings:
Fig. 1 is the overall structure schematic diagram described in the embodiment of the present invention;
Number in the figure: 1, suction port; 2, shell; 3, by-pass air duct; 4, main duct; 5, firing chamber; 6, low-pressure turbine; 7, puff prot; 8, high pressure turbine; 9, protecting crust; 10, high-pressure compressor; 11, low pressure compressor; 12, fan.
Embodiment
Below in conjunction with accompanying drawing, the preferred embodiments of the present invention are described, should be appreciated that preferred embodiment described herein is only for instruction and explanation of the present invention, is not intended to limit the present invention.
Embodiment: as shown in Figure 1,, a kind of chemical plant machinery turbojet architecture, comprise suction port 1, shell 2, by-pass air duct 3, main duct 4, firing chamber 5, low-pressure turbine 6, puff prot 7, high pressure turbine 8, protecting crust 9, high-pressure compressor 10, low pressure compressor 11 and fan 12; Described shell 2 one end is provided with suction port 1 and described shell 2 inside is provided with fan 12; Described fan 12 is installed on low compressor 11 inside and described low compressor 11 one end is connected with low-pressure turbine 6; Described low-pressure turbine 6 is connected with high pressure turbine 10 and high pressure turbine 8 one end is connected with high-pressure compressor 10; Firing chamber 5 is provided with between described low-pressure turbine 6 and high-pressure compressor 10.
As a kind of technical optimization scheme of the present invention: described casing 2 inside arranges by-pass air duct 3; Described high pressure turbine 8 and high-pressure compressor 10 surface are provided with protecting crust 9; Described protecting crust 9 outer surface arranges main duct 4; Described protecting crust 9 one end is provided with puff prot 7.
The present invention in use, the intake duct of what first air entered is motor, when aircraft flight, air-flow can be regarded as with flying speed flow direction engine, speed due to aircraft flight is change, and the speed of incoming flow that gas compressor adapts to has certain scope, thus the function of intake duct is exactly by adjustable pipe, and incoming flow is adjusted to suitable speed.When supersonic flight, before intake duct and in intake duct, airspeed reduces to subsonic speed, and now the stagnation of air-flow can make pressure raise tens times even tens times, and the pressure substantially exceeded in gas compressor improves multiple, thus create and depend merely on speed punching press, do not need the athodyd of gas compressor.Gas compressor after intake duct is the pressure being used for specially improving air-flow, and when air flows through gas compressor, compressor blade does work to air-flow, makes the pressure of air-flow, and temperature raises.When subsonic speed, gas compressor is the critical piece of air-flow supercharging.The high-temperature high-pressure fuel gas flowed out from turbine, continues to expand, to discharge backward along engine shaft to from spout at a high speed in jet pipe.The speed that this speed enters motor than air-flow is much bigger, makes motor obtain counteractive thrust.
Last it is noted that the foregoing is only the preferred embodiments of the present invention, be not limited to the present invention, although with reference to previous embodiment to invention has been detailed description, for a person skilled in the art, it still can be modified to the technological scheme described in foregoing embodiments, or carries out equivalent replacement to wherein portion of techniques feature.Within the spirit and principles in the present invention all, any amendment done, equivalent replacement, improvement etc., all should be included within protection scope of the present invention.
Claims (5)
1. a chemical plant machinery turbojet architecture, comprises suction port (1), shell (2), by-pass air duct (3), main duct (4), firing chamber (5), low-pressure turbine (6), puff prot (7), high pressure turbine (8), protecting crust (9), high-pressure compressor (10), low pressure compressor (11) and fan (12); It is characterized in that, described shell (2) one end is provided with suction port (1) and described shell (2) inside is provided with fan (12); Described fan (12) is installed on low compressor (11) inside and described low compressor (11) one end is connected with low-pressure turbine (6); Described low-pressure turbine (6) is connected with high pressure turbine (10) and high pressure turbine (8) one end is connected with high-pressure compressor (10); Firing chamber (5) is provided with between described low-pressure turbine (6) and high-pressure compressor (10).
2. a kind of chemical plant according to claim 1 machinery turbojet architecture, it is characterized in that, described casing (2) inside arranges by-pass air duct (3).
3. a kind of chemical plant according to claim 1 machinery turbojet architecture, is characterized in that, described high pressure turbine (8) and high-pressure compressor (10) surface are provided with protecting crust (9).
4. a kind of chemical plant according to claim 1 machinery turbojet architecture, it is characterized in that, described protecting crust (9) outer surface arranges main duct (4).
5. a kind of chemical plant according to claim 1 machinery turbojet architecture, it is characterized in that, described protecting crust (9) one end is provided with puff prot (7).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510479911.1A CN105065136A (en) | 2015-08-07 | 2015-08-07 | Mechanical equipment turbojet engine structure for chemical plant |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510479911.1A CN105065136A (en) | 2015-08-07 | 2015-08-07 | Mechanical equipment turbojet engine structure for chemical plant |
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| CN105065136A true CN105065136A (en) | 2015-11-18 |
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| CN201510479911.1A Pending CN105065136A (en) | 2015-08-07 | 2015-08-07 | Mechanical equipment turbojet engine structure for chemical plant |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108163171A (en) * | 2018-02-07 | 2018-06-15 | 济南大学 | Naval vessel propeller |
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2015
- 2015-08-07 CN CN201510479911.1A patent/CN105065136A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108163171A (en) * | 2018-02-07 | 2018-06-15 | 济南大学 | Naval vessel propeller |
| CN108163171B (en) * | 2018-02-07 | 2023-06-23 | 济南大学 | Ship propeller |
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Application publication date: 20151118 |