CN109339948A - Bullet gas-turbine unit inlet duct - Google Patents
Bullet gas-turbine unit inlet duct Download PDFInfo
- Publication number
- CN109339948A CN109339948A CN201811407133.5A CN201811407133A CN109339948A CN 109339948 A CN109339948 A CN 109339948A CN 201811407133 A CN201811407133 A CN 201811407133A CN 109339948 A CN109339948 A CN 109339948A
- Authority
- CN
- China
- Prior art keywords
- oil tank
- fuel oil
- turbine unit
- gas
- air intake
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
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Classifications
-
- 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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The invention proposes a kind of bullet gas-turbine unit inlet ducts.The device includes: fuel oil tank, connecting plate, air intake duct, deck store, connection cylinder and gas-turbine unit.Wherein: the back segment of fuel oil tank is in convergence shape, air intake duct is annular in shape, the inside of deck store has horn-like wall surface, fuel oil tank and horn-like wall surface constitute the internal channel of air intake duct, notch between fuel oil tank and deck store covering forms the import of air intake duct, it is fixedly connected between fuel oil tank and deck store using multichip connection plate, is fixedly connected between fuel oil tank and gas-turbine unit using connection cylinder.Bullet proposed by the present invention gas-turbine unit inlet duct, the prominent body surface of its air inlet thus there is good Stealth Fighter, and convenient for packaging, storage, transport and transmitting, circularly symmetric inlet charge efficiency is higher, and angle of attack characteristic and yaw angle characteristic are also preferable.
Description
Technical field
The present invention relates to technical field of aerospace, more particularly, to a kind of novel bullet gas-turbine unit inlet duct.
Background technique
With the fast development of the long-range strikes weapon such as cruising missile and unmanned plane, bullet with gas-turbine unit (including
Turbojet and turbofan) it is widely used in aviation due to its lasting cruising ability and fuel economy
Field.Because usually proposing stealthy war skill index request to guided missile, along with packaging, transport, latent penetrate with canister launch etc.
It is required that so guided missile is passed through frequently with Submerged Inlet and half Submerged Inlet as bullet gas-turbine unit air inlet dress
It sets.
But Submerged Inlet, compared to technique air intake duct and S-shaped air intake duct, exit flow field total pressure recovery coefficient is inclined
Low and distortion index is higher, this often will limit the performance of missile power system performance, and then the war skill that also will affect guided missile refers to
Mark.
So the problem relatively low for Submerged Inlet performance in the prior art, need a kind of new technical solution with
It solves the above problems.
Summary of the invention
In consideration of it, the present invention provides a kind of bullet combustion gas in order to solve at least one technical problem in the prior art
Turbogenerator inlet duct.
The device includes: fuel oil tank, connecting plate, air intake duct, deck store, connection cylinder and gas-turbine unit, in which:
Fuel oil tank, connecting plate, air intake duct, deck store, connection cylinder and gas-turbine unit, in which:
The back segment of fuel oil tank is in convergence shape；
Air intake duct is annular in shape；
The inside of deck store has horn-like wall surface；
Fuel oil tank and horn-like wall surface constitute the internal channel of air intake duct；
Notch between fuel oil tank and deck store covering forms the import of air intake duct；
It is fixedly connected between fuel oil tank and deck store using multichip connection plate；
It is fixedly connected between fuel oil tank and gas-turbine unit using connection cylinder.
In some embodiments, multichip connection plate is 4 symmetrical connecting plates of circumferential direction.
In some embodiments, before bullet gas-turbine unit emits, between the fuel oil tank and the deck store
Air intake duct import using glass blanking cover seal.
In some embodiments, when bullet gas-turbine unit ignition start, glass blanking cover is triggered using priming system
Crushing effect, the ignition start and just when so that glass blanking cover being ground into powder, without influencing bullet gas-turbine unit
Often work.
In some embodiments, connecting plate and connection cylinder, for fixing fuel oil tank and deck store, and allow electrical cable and
Fuel pipe passes through.
Bullet proposed by the present invention gas-turbine unit inlet duct, the not prominent body surface of air inlet thus tool
There is good Stealth Fighter, and convenient for packaging, storage, transport and transmitting, circularly symmetric inlet charge efficiency is higher, and
Angle of attack characteristic and yaw angle characteristic are also preferable.
Detailed description of the invention
In order to illustrate the technical solution of the embodiments of the present invention more clearly, will make below to required in the embodiment of the present invention
Attached drawing is briefly described, it is therefore apparent that drawings described below is only some embodiments of the present invention, for this
For the technical staff in field, without creative efforts, it can also be obtained according to these attached drawings other attached
Figure.
Fig. 1 is of the invention a kind of；The schematic diagram main view of circular section bomb body bullet gas-turbine unit inlet duct；
Fig. 2 is a kind of schematic diagram front view of circular section bomb body bullet gas-turbine unit inlet duct of the present invention；
Fig. 3 is a kind of schematic diagram side view of circular section bomb body bullet gas-turbine unit inlet duct of the present invention.
Wherein, cargo tank 1, connecting plate 2, air intake duct 3, deck store 4, connection cylinder 5 and gas-turbine unit 6.
Specific embodiment
In order to make the object, technical scheme and advantages of the embodiment of the invention clearer, below in conjunction with the embodiment of the present invention
In attached drawing, technical scheme in the embodiment of the invention is clearly and completely described.Obviously, described embodiment is
A part of the embodiment of the present invention, rather than whole embodiments.Based on the embodiments of the present invention, those skilled in the art
Without making creative work, every other embodiment obtained, shall fall within the protection scope of the present invention.
The feature and illustrative examples of various aspects of the invention is described more fully below.In following detailed description
In, many details are proposed, in order to provide complete understanding of the present invention.But come for those skilled in the art
It says it will be apparent that the present invention can be implemented in the case where not needing some details in these details.Below to reality
The description of example is applied just for the sake of providing and better understanding to of the invention by showing example of the invention.The present invention is never
It is limited to any specific setting and method set forth below, but covering finishes under the premise of without departing from the spirit of the present invention
Structure, method, any improvement of device, substitutions and modifications.In the the accompanying drawings and the following description, well known structure and skill is not shown
Art is unnecessary fuzzy to avoid causing to the present invention.
It should be noted that in the absence of conflict, the feature in the embodiment of the present invention and embodiment can be tied mutually
It closes, each embodiment mutually can be referred to and be quoted.The present invention will be described in detail below with reference to the accompanying drawings and embodiments.
Fig. 1 is of the invention a kind of；The schematic diagram main view of circular section bomb body bullet gas-turbine unit inlet duct；Figure
2 be a kind of schematic diagram front view of circular section bomb body bullet gas-turbine unit inlet duct of the present invention；Fig. 3 is the present invention one
The schematic diagram side view of kind circular section bomb body bullet gas-turbine unit inlet duct.
It please refers to shown in FIG. 1 to FIG. 3, the invention discloses a kind of novel bullet gas-turbine unit inlet duct, packets
Include fuel oil tank 1, connecting plate 2, air intake duct 3, deck store 4, connection cylinder 5 and gas-turbine unit 6.
As shown in FIG. 1 to 3,1 back segment of fuel oil tank is in convergence shape, the inside loudspeaker shape wall surface one with the deck store 4
Act the annular internal channel for constituting the air intake duct 3, the notch between 4 covering of fuel oil tank 1 and deck store formed cyclic annular air intake duct 3 into
Mouthful, and 4 circumferential directions can be used between fuel oil tank 1 and deck store 4 symmetrically the connecting plate 2 are fixedly connected, and fuel oil tank 1 with
It is fixedly connected between the gas-turbine unit 6 using the connection cylinder 5, it, can be in order to obtain better air inlet effect
It selects the diameter of deck store 4 bigger than the diameter of fuel oil tank 1, is conducive to incoming flow and flows into air intake duct in the form of punching press.
The import of air intake duct 3 before 6 ignition start of gas-turbine unit between fuel oil tank 1 and deck store 4 is preferentially adopted
It is sealed with glass blanking cover, it is special when gas-turbine unit ignition start using the crushing effect of priming system triggering glass blanking cover
Kind of glass blanking cover is ground into ignition start and normal work of the powder without influencing gas-turbine unit, and connecting plate 2 and even
Connecing the installations sections such as cylinder 5 can allow electrical cable and fuel pipe to pass through, guarantee missile power system mechanical interface, electric interfaces and
The normal mounting of communication interface.
It should be noted that the quantity of connecting plate 2 described in above-described embodiment is not limited to 4, and according to inlet characteristic
Demand and structural strength demand are not limited to circumferential be symmetrical arranged.
It should be noted that the blanking cover of air intake duct 3 described in above-described embodiment is not limited to the glass blanking cover form that can be crushed,
It is also possible to that the blanking cover comprising metal material and composite material put can be thrown.
Finally it should be noted that: the above embodiments are merely illustrative of the technical solutions of the present invention, but protection of the invention
Range is not limited thereto, and anyone skilled in the art in the technical scope disclosed by the present invention, can be thought easily
It is modified or replaceed to various equivalent, these, which are modified or replaceed, should all be included within the scope of the present invention.
Claims (5)
1. a kind of bullet gas-turbine unit inlet duct characterized by comprising
Fuel oil tank (1), connecting plate (2), air intake duct (3), deck store (4), connection cylinder (5) and gas-turbine unit (6),
In:
The back segment of fuel oil tank (1) is in convergence shape；
Air intake duct (3) is annular in shape；
The inside of deck store (4) has horn-like wall surface；
Fuel oil tank (1) and horn-like wall surface constitute the internal channel of air intake duct (3)；
Notch between fuel oil tank (1) and deck store (4) covering forms the import of air intake duct (3)；
It is fixedly connected between fuel oil tank (1) and deck store (4) using multichip connection plate (2)；
It is fixedly connected between fuel oil tank (1) and gas-turbine unit (6) using connection cylinder (5).
2. the apparatus according to claim 1, which is characterized in that wherein:
Multichip connection plate (2) is 4 symmetrical connecting plates of circumferential direction (2).
3. the apparatus according to claim 1, which is characterized in that wherein:
Before bullet gas-turbine unit emits, air intake duct (3) between the fuel oil tank (1) and the deck store (4)
Import is sealed using glass blanking cover.
4. the apparatus according to claim 1, which is characterized in that wherein:
When bullet gas-turbine unit ignition start, using the crushing effect of priming system triggering glass blanking cover, so that glass
Ignition start and normal work when blanking cover is ground into powder, without influencing bullet gas-turbine unit.
5. device described in any one of -4 according to claim 1, which is characterized in that wherein:
Connecting plate (2) and connection cylinder (5) for fixing fuel oil tank (1) and deck store (4), and allow electrical cable and fuel pipe
Road passes through.
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 true CN109339948A (en) | 2019-02-15 |
| CN109339948B CN109339948B (en) | 2021-01-08 |
Family
ID=65317564
Family Applications (1)
| 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 |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109339948B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113305214A (en) * | 2021-05-31 | 2021-08-27 | 四川航天长征装备制造有限公司 | Die for processing weakening groove of plugging part |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3684857A (en) * | 1970-02-05 | 1972-08-15 | Rolls Royce | Air intakes |
| EP0385294B1 (en) * | 1989-03-03 | 1992-04-15 | BMW ROLLS-ROYCE GmbH | Turbojet |
| US20020023428A1 (en) * | 2000-08-28 | 2002-02-28 | Jean-Paul Demay | Blanking-cap system for an orifice of a conduit, in particular for an orifice of an air-intake duct into the combustion chamber of a ramjet |
| 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 |
-
2018
- 2018-11-23 CN CN201811407133.5A patent/CN109339948B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3684857A (en) * | 1970-02-05 | 1972-08-15 | Rolls Royce | Air intakes |
| EP0385294B1 (en) * | 1989-03-03 | 1992-04-15 | BMW ROLLS-ROYCE GmbH | Turbojet |
| US20020023428A1 (en) * | 2000-08-28 | 2002-02-28 | Jean-Paul Demay | Blanking-cap system for an orifice of a conduit, in particular for an orifice of an air-intake duct into the combustion chamber of a ramjet |
| 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 |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113305214A (en) * | 2021-05-31 | 2021-08-27 | 四川航天长征装备制造有限公司 | Die for processing weakening groove of plugging part |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109339948B (en) | 2021-01-08 |
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