CN109339948B - Gas turbine engine air inlet device for bombs - Google Patents
Gas turbine engine air inlet device for bombs Download PDFInfo
- Publication number
- CN109339948B CN109339948B CN201811407133.5A CN201811407133A CN109339948B CN 109339948 B CN109339948 B CN 109339948B CN 201811407133 A CN201811407133 A CN 201811407133A CN 109339948 B CN109339948 B CN 109339948B
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- Prior art keywords
- cabin
- turbine engine
- gas turbine
- air inlet
- fuel oil
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
Abstract
The invention provides an air inlet device of a gas turbine engine for bombs. The device includes: the gas turbine engine comprises a fuel oil cabin, a connecting plate, an air inlet channel, a tail cabin, a connecting cylinder and a gas turbine engine. Wherein: the rear section of the fuel oil cabin is in a convergent shape, the air inlet channel is in an annular shape, a horn-shaped wall surface is arranged inside the tail cabin, the fuel oil cabin and the horn-shaped wall surface form an inner channel of the air inlet channel, a gap between the fuel oil cabin and the skin of the tail cabin forms an inlet of the air inlet channel, the fuel oil cabin and the tail cabin are fixedly connected through a plurality of connecting plates, and the fuel oil cabin and the gas turbine engine are fixedly connected through a connecting cylinder. The gas inlet of the gas turbine engine for bombs provided by the invention has good stealth performance because the gas inlet does not protrude out of the surface of the bomb body, is convenient for packaging, storage, transportation and launching, and has higher gas inlet efficiency, better attack angle characteristic and side slip angle characteristic due to the annular symmetrical gas inlet.
Description
Technical Field
The invention relates to the technical field of aviation, in particular to a novel gas turbine engine air inlet device for a bomb.
Background
With the rapid development of long-distance hitting weapons such as flying missiles and unmanned planes, gas turbine engines for missiles (including turbojet engines and turbofan engines) are widely applied to the aviation field due to the long-lasting cruising ability and fuel economy. Because stealth tactical index requirements are generally provided for the missile, and requirements such as packaging, transportation, submarine firing, box type launching and the like are added, the missile often adopts an embedded air inlet channel and a semi-embedded air inlet channel as an air inlet device of a gas turbine engine for the missile.
However, compared with a process air inlet and an S-shaped air inlet, the total pressure recovery coefficient of an outlet flow field of the embedded air inlet is lower and the distortion index is higher, which often limits the performance of a missile power system and further affects the tactical indexes of the missile.
Therefore, a new technical solution is needed to solve the above-mentioned problem of the prior art that the performance of the buried intake duct is low.
Disclosure of Invention
In view of the above, to solve at least one technical problem in the prior art, the present invention provides an intake device for a gas turbine engine for bombs.
The device includes: fuel oil cabin, connecting plate, intake duct, tail-room, connection drum and gas turbine engine, wherein:
fuel oil cabin, connecting plate, intake duct, tail-room, connection drum and gas turbine engine, wherein:
the rear section of the fuel oil cabin is in a convergent shape;
the air inlet channel is annular;
the interior of the tail cabin is provided with a horn-shaped wall surface;
the fuel oil cabin and the horn-shaped wall surface form an inner channel of the air inlet channel;
a gap between the fuel oil cabin and the tail cabin skin forms an inlet of an air inlet channel;
the fuel oil cabin is fixedly connected with the tail cabin by a plurality of connecting plates;
the fuel oil cabin and the gas turbine engine are fixedly connected by a connecting cylinder.
In some embodiments, the plurality of webs is 4 webs that are circumferentially symmetric.
In some embodiments, an inlet of the air intake passage between the fuel compartment and the tail compartment is sealed with a glass cap prior to firing of the gas turbine engine.
In some embodiments, when the gas turbine engine for the bomb is ignited to start, the initiating explosive device is used for triggering the crushing effect of the glass blocking cover, so that the glass blocking cover is crushed into powder without influencing the ignition start and the normal operation of the gas turbine engine for the bomb.
In some embodiments, a connecting plate and connecting cylinder are used to secure the fuel tank to the tail tank and to allow the passage of electrical cables and fuel lines.
The gas inlet of the gas turbine engine for bombs provided by the invention has good stealth performance because the gas inlet does not protrude out of the surface of the bomb body, is convenient for packaging, storage, transportation and launching, and has higher gas inlet efficiency, better attack angle characteristic and side slip angle characteristic due to the annular symmetrical gas inlet.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments of the present invention will be briefly described below, and it is obvious that the drawings described below are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
FIG. 1 is a schematic front view of a gas turbine engine intake for a round section missile of the present invention;
FIG. 2 is a schematic front view of a gas turbine engine intake for a round section projectile of the present invention;
fig. 3 is a schematic side view of a gas turbine engine intake for a round section projectile of the present invention.
The gas turbine engine comprises an oil tank 1, a connecting plate 2, an air inlet 3, a tail tank 4, a connecting cylinder 5 and a gas turbine engine 6.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention. It is to be understood that the embodiments described are only a few embodiments of the present invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Features and illustrative embodiments of various aspects of the invention are described in detail below. In the following detailed description, numerous specific details are set forth in order to provide a thorough understanding of the present invention. It will be apparent, however, to one skilled in the art that the present invention may be practiced without some of these specific details. The following description of the embodiments is merely intended to provide a better understanding of the present invention by illustrating examples of the present invention. The present invention is in no way limited to any specific arrangement and method set forth below, but rather covers any improvements, substitutions and modifications in structure, method, and apparatus without departing from the spirit of the invention. In the drawings and the following description, well-known structures and techniques are not shown to avoid unnecessarily obscuring the present invention.
It should be noted that, in the case of conflict, the embodiments and features of the embodiments of the present invention may be combined with each other, and the respective embodiments may be mutually referred to and cited. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
FIG. 1 is a schematic front view of a gas turbine engine intake for a round section missile of the present invention; FIG. 2 is a schematic front view of a gas turbine engine intake for a round section projectile of the present invention; fig. 3 is a schematic side view of a gas turbine engine intake for a round section projectile of the present invention.
Referring to fig. 1 to 3, the invention discloses a novel gas turbine engine air inlet device for a bomb, which comprises a fuel oil cabin 1, a connecting plate 2, an air inlet channel 3, a tail cabin 4, a connecting cylinder 5 and a gas turbine engine 6.
As shown in fig. 1-3, the rear section of the fuel oil cabin 1 is convergent, and forms an annular inner channel of the air inlet channel 3 together with the inner horn-shaped wall surface of the tail cabin 4, a gap between the fuel oil cabin 1 and the skin of the tail cabin 4 forms an inlet of the annular air inlet channel 3, 4 pieces of circumferentially symmetrical connecting plates 2 can be used between the fuel oil cabin 1 and the tail cabin 4, the fuel oil cabin 1 and the gas turbine engine 6 are fixedly connected by the connecting cylinder 5, and in order to obtain a better air inlet effect, the diameter of the tail cabin 4 can be selected to be larger than that of the fuel oil cabin 1, so that incoming flow can flow into the air inlet channel in a stamping manner.
The inlet of an air inlet channel 3 between a fuel oil cabin 1 and a tail cabin 4 is preferably sealed by a glass blanking cover before the ignition starting of a gas turbine engine 6, when the ignition starting of the gas turbine engine is carried out, an initiating explosive device is utilized to trigger the crushing effect of the glass blanking cover, the special glass blanking cover is crushed into powder without influencing the ignition starting and the normal work of the gas turbine engine, and the connecting plate 2, the connecting cylinder 5 and other installation joints can allow an electric cable and a fuel oil pipeline to pass through, so that the normal installation of a mechanical interface, an electric interface and a communication interface of a missile power system is ensured.
It should be noted that, in the above embodiment, the number of the connecting plates 2 is not limited to 4, and the connecting plates are not limited to be circumferentially symmetrically arranged according to the performance requirement and the structural strength requirement of the air inlet.
It should be noted that the cover of the air inlet 3 in the above embodiments is not limited to a shatterable glass cover, but may be a disposable cover containing a metal material and a composite material.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solutions of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art can easily conceive various equivalent modifications or substitutions within the technical scope of the present invention, and these modifications or substitutions should be covered within the scope of the present invention.
Claims (4)
1. A gas turbine engine intake for a bomb, comprising:
fuel oil cabin (1), connecting plate (2), intake duct (3), tail cabin (4), connection drum (5) and gas turbine engine (6), wherein:
the rear section of the fuel oil cabin (1) is convergent;
the air inlet channel (3) is annular and is an annular embedded air inlet channel;
the interior of the tail cabin (4) is provided with a horn-shaped wall surface;
the fuel oil cabin (1) and the horn-shaped wall surface form an inner channel of the air inlet channel (3);
a gap between the fuel oil cabin (1) and the skin of the tail cabin (4) forms an inlet of the air inlet channel (3);
the fuel oil cabin (1) and the tail cabin (4) are fixedly connected by a plurality of connecting plates (2);
the fuel oil cabin (1) and the gas turbine engine (6) are fixedly connected by a connecting cylinder (5).
2. The apparatus of claim 1, wherein:
the plurality of connecting plates (2) are 4 connecting plates (2) which are circumferentially symmetrical.
3. The apparatus of claim 1, wherein:
before the bomb gas turbine engine launches, the inlet of the air inlet channel (3) between the fuel oil cabin (1) and the tail cabin (4) is sealed by a glass plug cover.
4. The apparatus of any one of claims 1-3, wherein:
the connecting plate (2) and the connecting cylinder (5) are also used for passing through an electric cable and a fuel pipeline.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811407133.5A CN109339948B (en) | 2018-11-23 | 2018-11-23 | Gas turbine engine air inlet device for bombs |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811407133.5A CN109339948B (en) | 2018-11-23 | 2018-11-23 | Gas turbine engine air inlet device for bombs |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109339948A CN109339948A (en) | 2019-02-15 |
| CN109339948B true CN109339948B (en) | 2021-01-08 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811407133.5A Active CN109339948B (en) | 2018-11-23 | 2018-11-23 | Gas turbine engine air inlet device for bombs |
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Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113305214B (en) * | 2021-05-31 | 2022-11-29 | 四川航天长征装备制造有限公司 | Die for processing weakening groove of plugging part |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2103035C3 (en) * | 1970-02-05 | 1975-03-27 | Secretary Of State For Defence Of The United Kingdom Of Great Britain And Northern Ireland, London | Air inlet for gas turbine engines |
| DE3906765A1 (en) * | 1989-03-03 | 1990-09-06 | Kloeckner Humboldt Deutz Ag | TURBO STEEL ENGINE |
| FR2813344B1 (en) * | 2000-08-28 | 2002-11-29 | Aerospatiale Matra Missiles | BLINDING SYSTEM FOR A DUCT ORIFICE, PARTICULARLY FOR AN ORIFICE OF AN AIR INTAKE PATHWAY IN THE COMBUSTION CHAMBER OF A STATOREACTOR |
| CN105129096A (en) * | 2015-07-14 | 2015-12-09 | 洛阳大智实业有限公司 | Novel dual-power tandem loitering powerplant |
| CN107762633A (en) * | 2017-09-15 | 2018-03-06 | 江西洪都航空工业集团有限责任公司 | Bullet high-performance Submerged Inlet and boundary-layer minimizing technology |
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