CN106593694B

CN106593694B - A kind of centripetal turbine fan jet engine

Info

Publication number: CN106593694B
Application number: CN201611206460.5A
Authority: CN
Inventors: 李可
Original assignee: Individual
Current assignee: Individual
Priority date: 2016-12-23
Filing date: 2016-12-23
Publication date: 2018-03-20
Anticipated expiration: 2036-12-23
Also published as: CN106593694A

Abstract

The invention discloses a kind of centripetal turbine fan jet engine, belong to engine art.A kind of centripetal turbine fan jet engine, including main shaft, shell and annular firing chamber enclosure, the front-end of spindle is fixedly connected with front support blade, the one end of the front support blade away from main shaft is connected with case nose inwall, the main shaft tail end is fixedly connected with tail bone, rear support blade is fixed with the tail bone, the described one end of rear support blade away from tail bone is connected with outer casing inner wall, combuster is fixedly connected with the main shaft and fixes blade, the combustion chamber is fixed the one end of blade away from main shaft and is connected with toroidal combustion chamber case nose inwall.It can realize multi-stage booster, provided with internal duct and external duct is completely independent, main duct air inlet need not consider by-pass air duct blade design, only need to consider main duct air inlet and increasing compression ratio, as long as by-pass air duct fan blade considers to improve air inflow and efficiency under engine general power, the provided with internal duct and external duct blade of engine optimizes.

Description

A kind of centripetal turbine fan jet engine

Technical field

The present invention relates to engine art, more specifically to a kind of centripetal turbine fan jet engine.

Background technology

Existing turbojet engine has centrifugal turbojet engine, axial flow turbojet two types, centrifugal whirlpool Fuel-injection engine single stage supercharging is simple in construction than big, but sectional area is big windward, is not suitable for doing multi-stage booster or turbofan structure；Axle stream The total pressure ratio of formula turbojet engine is big, and efficiency high, sectional area is small windward, can do multi-stage booster and add turbofan structure, but complicated, Front and rear force(d) (draft) fan and provided with internal duct and external duct fan influences each other, and needs to compromise mutually in design.

The content of the invention

1. technical problems to be solved

Be not suitable for doing multi-stage booster or turbofan structure, axial-flow type for centrifugal turbojet engine present in prior art Turbojet engine is complicated, mutual compromise problem is needed in design, it is an object of the invention to provide a kind of centripetal turbine Fan jet engine, it can realize multi-stage booster, and provided with internal duct and external duct is completely independent without compromise mutually in design.

2. technical scheme

To solve the above problems, the present invention adopts the following technical scheme that.

A kind of centripetal turbine fan jet engine, including main shaft, shell and annular firing chamber enclosure, the main shaft Front end is fixedly connected with front support blade, and the one end of the front support blade away from main shaft is connected with case nose inwall, described Main shaft tail end is fixedly connected with tail bone, rear support blade is fixed with the tail bone, the rear support blade is away from tail bone One end is connected with outer casing inner wall, and front support blade and rear support blade play a part of main shaft and shell to fix, the main shaft On be fixedly connected with combuster and fix blade, the combustion chamber fix the one end of blade away from main shaft with before annular firing chamber enclosure End inwall is connected, and annular flame tube, the annular flame tube front end and combustion are provided between main shaft and the annular firing chamber enclosure Burn room fixation blade to be connected, outer ring afterbody and the annular firing chamber enclosure of the annular flame tube are fixedly linked, the ring-shaped fire Mutually fixed by the first guide vane between the inner ring afterbody of flame cylinder and annular firing chamber enclosure, the annular flame tube inner ring tail Mutually fixed by oblate centrum between portion and main shaft, the first leaf dish is rotatably connected to by clutch shaft bearing on the main shaft, it is described First leaf dish is provided with fan type flabellum, and the described one end of fan type flabellum away from the first leaf dish is fixedly connected with gas compressor blade Spiral blade is distributed with wheel, the compressor impeller inwall concentric circumferences, and the spiral blade is by compressor impeller outer rim Clockwise direction center convolution is shunk, and the spiral blade is located at one end and the fan type flabellum phase of compressor impeller inwall afterbody Even, the compressor impeller end is fixedly connected with sleeve, and the sleeve gradually expands to main shaft tail and fully wrapped around annular Combustor outer casing, the second leaf dish is rotatably connected to by second bearing on the main shaft, second leaf dish is provided with turbine leaf Piece, the one end of the turbo blade away from the second leaf dish are connected with barrel end inwall, and the compressor impeller outer wall afterbody is set There is the first order fan blade with the distribution of main shaft concentric circumferences, the sleeve outer wall middle part and afterbody are respectively equipped with concentric with main shaft The second level fan blade and third level fan blade of circle distribution, first order fan blade, second level fan blade and the 3rd Level fan blade collectively constitutes the three-level force(d) (draft) fan of by-pass air duct, realizes the spiral shell of multi-stage booster, compressor impeller and its inside Rotation shape blade, fan type flabellum collectively constitute main duct, and provided with internal duct and external duct is completely independent, and main duct air inlet need not consider by-pass air duct leaf Piece designs, it is only necessary to main duct air inlet and increasing compression ratio is considered, as long as by-pass air duct fan blade is considered under engine general power Air inflow and efficiency are improved, the provided with internal duct and external duct blade for realizing engine optimizes.

Preferably, front support stand and rear support stand, the front support stand and rear support stand are fixedly connected with the shell It is each attached on base, engine is fixed on base by front support stand and rear support stand, plays entire engine and fix Effect.

Preferably, the shell parcel compressor impeller and sleeve, the outer casing inner wall are fixedly connected with the second water conservancy diversion leaf Piece and the 3rd guide vane, second guide vane are described between first order fan blade and second level fan blade 3rd guide vane between second level fan blade and third level fan blade, shell formed in compressor impeller front end into Gas passage, air enters engine by-pass air duct, the second guide vane and the 3rd guide vane by inlet channel to be carried out to air Water conservancy diversion.

Preferably, the front-end of spindle offers fuel tube, and the combustion chamber is fixed on blade and offers fuel Spout and hollow pipeline, and fuel nozzle ports are located in annular flame tube, described hollow pipeline one end communicates with fuel tube, The other end of the hollow pipeline is communicated with fuel nozzle ports, and fuel is delivered fuel into by fuel tube and hollow pipeline Spout, fuel is sprayed into annular flame tube.

Preferably, fuel tube is offered in the main shaft, offers cavity in the annular firing chamber enclosure, institute State and offer fuel nozzle ports and hollow pipeline on combustion chamber fixation blade, described hollow pipeline one end communicates with cavity, in described The other end of vacant duct is communicated with fuel nozzle ports, and the economizer bank communicated is offered in the oblate centrum and the first guide vane Road, described preheating pipe one end communicate with the fuel tube in main shaft, and the other end of the preheating pipe communicates with cavity, By fuel tube, preheating pipe, chamber cavity delivers fuel into fuel nozzle ports, and fuel is fired by pipeline and annular Burn chamber enclosure to be preheated, strengthen atomizing effect, improve efficiency of combustion, annular firing chamber enclosure internal cavity is effectively reduced ring The weight of shape combustor outer casing, preheating of fuel effectively reduce combustor outer casing temperature.

3. beneficial effect

Compared to prior art, the advantage of the invention is that：

（1）This programme first order fan blade, second level fan blade and third level fan blade collectively constitute by-pass air duct Three-level force(d) (draft) fan, realize multi-stage booster, spiral blade, common group of the fan type flabellum of compressor impeller and its inside Into main duct, provided with internal duct and external duct is completely independent, and main duct air inlet need not consider by-pass air duct blade design, it is only necessary to considers that main duct enters Gas and increasing compression ratio, as long as by-pass air duct fan blade considers to improve air inflow and efficiency under engine general power, realize hair The provided with internal duct and external duct blade of motivation optimizes.

（2）Engine is fixed on base by front support stand and rear support stand, plays the work of entire engine fixation With.

（3）Shell forms inlet channel in compressor impeller front end, and air enters engine by-pass air duct by inlet channel, Second guide vane and the external bypass air of the 3rd guide vane carry out water conservancy diversion.

（4）Fuel nozzle ports are delivered fuel into by fuel tube and hollow pipeline, sprayed into annular flame tube Fuel.

（5）By fuel tube, preheating pipe, chamber cavity delivers fuel into fuel nozzle ports, and fuel passes through Pipeline and annular firing chamber enclosure are preheated, enhancing atomizing effect, raising efficiency of combustion, the cavity in annular firing chamber enclosure The weight of annular firing chamber enclosure is effectively reduced, preheating of fuel effectively reduces combustor outer casing temperature.

Brief description of the drawings

Fig. 1 is the diagrammatic cross-section of the present invention；

Fig. 2 is the front view of the present invention；

Fig. 3 is the rearview of the present invention；

Fig. 4 is the chamber structure schematic diagram of the present invention；

Fig. 5 is the main axle structure schematic diagram of the present invention；

Fig. 6 is one of combustion chamber profile of the present invention；

Fig. 7 is the structural representation at A in Fig. 6；

Fig. 8 is one of combustion chamber cross-sectional view of the present invention.

Label declaration in figure：

Blade, 5 annular firing chamber enclosures, 6 sleeves, 7 are fixed in 1 main shaft, 2 spiral blades, 3 compressor impellers, 4 combustion chambers Turbo blade, 8 second leaf dishes, 9 tail bones, 10 shells, 11 bases, 12 rear support blades, 13 rear support stands, 14 third level fan leafs Piece, 15 annular flame tubes, 16 second level fan blade, 17 first order fan blade, 18 front support stands, 19 fan type flabellums, 20 First leaf dish, 21 front support blades, 22 first guide vanes, 23 oblate centrums, 24 fuel tubes, 25 hollow pipelines, 26 Fuel nozzle ports, 27 preheating pipes, 28 cavitys.

Embodiment

Below in conjunction with the accompanying drawing in the embodiment of the present invention；Technical scheme in the embodiment of the present invention is carried out clear, complete Site preparation describes；Obviously；Described embodiment is only part of the embodiment of the present invention；Rather than whole embodiment.It is based on Embodiment in the present invention；Those of ordinary skill in the art are obtained every other under the premise of creative work is not made Embodiment；Belong to the scope of protection of the invention.

Embodiment 1：

Refer to Fig. 1-8, a kind of centripetal turbine fan jet engine, including main shaft 1, shell 10 and annular firing Chamber enclosure 5, the front end of main shaft 1 are fixedly connected with front support blade 21, the one end of front support blade 21 away from main shaft 1 with before shell 10 End inwall is connected, and the tail end of main shaft 1 is fixedly connected with tail bone 9, and rear support blade 12, rear support blade 12 are fixed with tail bone 9 One end away from tail bone 9 is connected with the inwall of shell 10, and front support stand 18 and rear support stand 13, preceding branch are fixedly connected with shell 10 Support 18 and rear support stand 13 are each attached on base 11, front support blade 21 and rear support blade 12 play a main shaft 1 with it is outer The effect that shell 10 is fixed, engine is fixed on the pedestal 11 by front support stand 18 and rear support stand 13, play overall start The effect that machine is fixed.

Combuster is fixedly connected with main shaft 1 and fixes blade 4, the one end of blade 4 away from main shaft 1 and annular are fixed in combustion chamber The front inner wall of combustor outer casing 5 is connected, and annular flame tube 15, annular flame tube are provided between main shaft 1 and annular firing chamber enclosure 5 15 front ends are fixed blade 4 with combustion chamber and are connected, and outer ring afterbody and the annular firing chamber enclosure 5 of annular flame tube 15 are fixedly linked, Fixed between the inner ring afterbody of annular flame tube 15 and annular firing chamber enclosure 5 by the phase of the first guide vane 22, annular flame Fixed between 15 inner ring afterbodys of cylinder and main shaft 1 by the oblate phase of centrum 23, the front end of main shaft 1 offers fuel tube 24, combustion Burn and offer fuel nozzle ports 26 and hollow pipeline 25 on room fixation blade 4, and fuel nozzle ports 26 are located in annular flame tube 15, in The one end of vacant duct 25 communicates with fuel tube 24, and the other end of hollow pipeline 25 communicates with fuel nozzle ports 26, passes through fuel Conveyance conduit 24 and hollow pipeline 25 deliver fuel into fuel nozzle ports 26, and fuel, combustion chamber are sprayed into annular flame tube 15 Fixed blade 4, the first guide vane 22 and oblate centrum 23 play a part of main shaft 1 and fixed with the phase of annular firing chamber enclosure 5, ring Air admission hole is provided with shape burner inner liner 15, is easy to air to enter burner inner liner 15, so that combustion gas is fully burnt.

First leaf dish 20 is rotatably connected to by clutch shaft bearing on main shaft 1, the first leaf dish 20 is provided with fan type flabellum 19, The one end of fan type flabellum 19 away from the first leaf dish 20 is fixedly connected with compressor impeller 3, the inwall concentric circumferences of compressor impeller 3 Spiral blade 2 is distributed with, spiral blade 2 is shunk by the outer rim clockwise direction center convolution of compressor impeller 3, compressor impeller Gathered during 3 rotate counterclockwise by export-oriented center, compressed air, spiral blade 2 is located at one end of the inwall afterbody of compressor impeller 3 It is connected with fan type flabellum 19, spiral blade 2, the fan type flabellum 19 of compressor impeller 3 and its inside collectively constitute intension Road, the end of compressor impeller 3 are fixedly connected with sleeve 6, and sleeve 6 gradually expands to the afterbody of main shaft 1 and fully wrapped around annular firing Chamber enclosure 5, the second leaf dish 8 is rotatably connected to by second bearing on main shaft 1, the second leaf dish 8 is provided with turbo blade 7, turbine The one end of blade 7 away from the second leaf dish 8 is connected with the inner wall at end of sleeve 6, and the outer wall afterbody of compressor impeller 3 is provided with same with main shaft 1 The first order fan blade 17 of heart circle distribution, in the middle part of the outer wall of sleeve 6 and afterbody is respectively equipped with and the concentric circumferences of main shaft 1 are distributed Second level fan blade 16 and third level fan blade 14, first order fan blade 17, second level fan blade 16 and the third level Fan blade 14 collectively constitutes the three-level force(d) (draft) fan of by-pass air duct, realizes multi-stage booster, and provided with internal duct and external duct is completely independent, intension Road air inlet need not consider by-pass air duct blade design, it is only necessary to consider main duct air inlet and increasing compression ratio, by-pass air duct fan blade As long as considering to improve air inflow and efficiency under engine general power, the provided with internal duct and external duct blade for realizing engine optimizes,

Shell 10 wraps up compressor impeller 3 and sleeve 6, the inwall of shell 10 are fixedly connected with the second guide vane and the 3rd and led Blade is flowed, the second guide vane is between first order fan blade 17 and second level fan blade 16, the 3rd guide vane position Between second level fan blade 16 and third level fan blade 14, shell 10 forms inlet channel in the front end of compressor impeller 3, Air enters engine by-pass air duct, the second guide vane and the 3rd guide vane by inlet channel and carries out water conservancy diversion to air.

Operation principle：First leaf dish 20 and the second leaf dish 8 rotate phase by clutch shaft bearing and second bearing with main shaft 1 respectively Even, the first leaf dish 20 is fixedly linked with compressor impeller 3, and the second leaf dish 8 is fixedly linked by turbo blade 7 and sleeve 6, is opened During engine start switch, compressor impeller 3 is around the rotate counterclockwise of main shaft 1, and compressor impeller 3 is with moving sleeve 6 around 1 turn of main shaft Dynamic, by-pass air duct first order fan blade 17, second level fan blade 16 and third level fan blade 14 follow the and of compressor impeller 3 Sleeve 6 rotates, and sucks air from Way in, air divides two parts, and a part increases from by-pass air duct by the compression of moderate breeze fan leaf Pressure is directly entered jet pipe, and another part is gathered in 3 rotate counterclockwise of compressor impeller by the export-oriented center of compressor impeller 3, It is pressurized by compressor impeller 3 into combustion chamber, air and annular flame tube 15 is entered by the passage on annular flame tube 15, is fired Material is transported to annular flame tube 15 by fuel tube 24, so as to fuel and air mixed combustion, forms HTHP Combustion gas sprays backward, and promotes turbo blade 7 to be rotated around main shaft 1 and do work, and turbo blade 7 rotates with moving sleeve 6 around main shaft 1, covers Cylinder 6 drives compressor impellers 3 to be rotated around main shaft 1, so as to by-pass air duct first order fan blade 17, second level fan blade 16 and the Three-level fan blade 14 follows compressor impeller 3 and sleeve 6 to rotate, and forms circular work process, the high-temperature high-pressure fuel gas of ejection With the cold air by by-pass air duct supercharging ejection is mixed in jet pipe.

Embodiment 2：

A kind of centripetal turbine fan jet engine, it is same as Example 1, except that, offered in main shaft 1 Fuel tube 24, cavity 28 is offered in annular firing chamber enclosure 5, and combustion chamber is fixed on blade 4 and offers fuel nozzle ports 26 and hollow pipeline 25, the one end of hollow pipeline 25 communicated with cavity 28, the other end of hollow pipeline 25 communicates with fuel nozzle ports 26, Offer the preheating pipe 27 communicated in the oblate guide vane 22 of centrum 23 and first, the one end of preheating pipe 27 with main shaft 1 Fuel tube 24 communicates, and the other end of preheating pipe 27 communicates with cavity 28, passes through fuel tube 24, preheating pipe 27, chamber cavity 28 delivers fuel into fuel nozzle ports 26, and fuel is preheated by pipeline and annular firing chamber enclosure 5, Strengthen atomizing effect, improve efficiency of combustion, the cavity in annular firing chamber enclosure 5 is effectively reduced annular firing chamber enclosure 5 Weight, preheating of fuel effectively reduces the temperature of combustor outer casing 5.

It is described above；Preferable embodiment only of the invention；But protection scope of the present invention is not limited thereto； Any one skilled in the art the invention discloses technical scope in；Technique according to the invention scheme and its Improve design and be subject to equivalent substitution or change；It should all cover within the scope of the present invention.

Claims

1. a kind of centripetal turbine fan jet engine, including main shaft（1）, shell（10）With annular firing chamber enclosure（5）, It is characterized in that：The main shaft（1）Front end is fixedly connected with front support blade（21）, the front support blade（21）Away from main shaft （1）One end and shell（10）Front inner wall is connected, the main shaft（1）Tail end is fixedly connected with tail bone（9）, the tail bone（9） On be fixed with rear support blade（12）, the rear support blade（12）Away from tail bone（9）One end and shell（10）Inwall phase Even, the main shaft（1）On be fixedly connected combuster fix blade（4）, blade is fixed in the combustion chamber（4）Away from main shaft（1） One end and annular firing chamber enclosure（5）Front inner wall is connected, the main shaft（1）With annular firing chamber enclosure（5）Between be provided with Annular flame tube（15）, the annular flame tube（15）Blade is fixed in front end with combustion chamber（4）It is connected, the annular flame tube （15）Outer ring afterbody and annular firing chamber enclosure（5）It is fixedly linked, the annular flame tube（15）Inner ring afterbody with annular Combustor outer casing（5）Between pass through the first guide vane（22）It is mutually fixed, the annular flame tube（15）Inner ring afterbody and main shaft （1）Between pass through oblate centrum（23）It is mutually fixed, the main shaft（1）It is upper that first leaf dish is rotatably connected to by clutch shaft bearing （20）, first leaf dish（20）It is provided with fan type flabellum（19）, the fan type flabellum（19）Away from the first leaf dish（20） One end be fixedly connected with compressor impeller（3）, the compressor impeller（3）Spiral blade is distributed with inwall concentric circumferences （2）, the spiral blade（2）By compressor impeller（3）Outer rim clockwise direction center convolution is shunk, the spiral blade （2）Positioned at compressor impeller（3）One end of inwall afterbody and fan type flabellum（19）It is connected, the compressor impeller（3）End It is fixedly connected with sleeve（6）, the sleeve（6）To main shaft（1）Afterbody gradually expands and fully wrapped around annular firing chamber enclosure （5）, the main shaft（1）It is upper that second leaf dish is rotatably connected to by second bearing（8）, second leaf dish（8）It is provided with turbine Blade（7）, the turbo blade（7）Away from the second leaf dish（8）One end and sleeve（6）Inner wall at end is connected, the compressor Impeller（3）Outer wall afterbody is provided with and main shaft（1）The first order fan blade of concentric circumferences distribution（17）, the sleeve（6）Outer wall Middle part and afterbody are respectively equipped with and main shaft（1）The second level fan blade of concentric circumferences distribution（16）With third level fan blade （14）.

A kind of 2. centripetal turbine fan jet engine according to claim 1, it is characterised in that：The shell （10）On be fixedly connected with front support stand（18）And rear support stand（13）, the front support stand（18）And rear support stand（13）It is solid It is scheduled on base（11）On.

A kind of 3. centripetal turbine fan jet engine according to claim 1 or 2, it is characterised in that：It is described outer Shell（10）Wrap up compressor impeller（3）And sleeve（6）, the shell（10）Inwall is fixedly connected with the second guide vane and the 3rd Guide vane, second guide vane are located at first order fan blade（17）With second level fan blade（16）Between, it is described 3rd guide vane is located at second level fan blade（16）With third level fan blade（14）Between.

A kind of 4. centripetal turbine fan jet engine according to claim 1, it is characterised in that：The main shaft （1）Front end offers fuel tube（24）, blade is fixed in the combustion chamber（4）On offer fuel nozzle ports（26）With it is hollow Pipeline（25）, and fuel nozzle ports（26）Positioned at annular flame tube（15）It is interior, the hollow pipeline（25）One end and fuel -supply pipe Road（24）Communicate, the hollow pipeline（25）The other end and fuel nozzle ports（26）Communicate.

A kind of 5. centripetal turbine fan jet engine according to claim 1, it is characterised in that：The main shaft （1）Inside offer fuel tube（24）, the annular firing chamber enclosure（5）Inside offer cavity（28）, the combustion chamber Fixed blade（4）On offer fuel nozzle ports（26）And hollow pipeline（25）, the hollow pipeline（25）One end and cavity（28） Communicate, the hollow pipeline（25）The other end and fuel nozzle ports（26）Communicate, the oblate centrum（23）With the first water conservancy diversion leaf Piece（22）Inside offer the preheating pipe communicated（27）, the preheating pipe（27）One end and main shaft（1）Interior fuel -supply pipe Road（24）Communicate, the preheating pipe（27）The other end and cavity（28）Communicate.