CN115355103A - Tail jet pipe structure suitable for double-duct turbofan engine - Google Patents
Tail jet pipe structure suitable for double-duct turbofan engine Download PDFInfo
- Publication number
- CN115355103A CN115355103A CN202210910634.5A CN202210910634A CN115355103A CN 115355103 A CN115355103 A CN 115355103A CN 202210910634 A CN202210910634 A CN 202210910634A CN 115355103 A CN115355103 A CN 115355103A
- Authority
- CN
- China
- Prior art keywords
- cartridge receiver
- duct
- turbofan engine
- linking bridge
- engine
- 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.)
- Pending
Links
- 230000009977 dual effect Effects 0.000 claims description 5
- 230000013011 mating Effects 0.000 claims 1
- 230000009286 beneficial effect Effects 0.000 description 9
- 238000007789 sealing Methods 0.000 description 5
- 238000003466 welding Methods 0.000 description 3
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 230000002035 prolonged effect Effects 0.000 description 2
- 239000007921 spray Substances 0.000 description 2
- 238000005299 abrasion Methods 0.000 description 1
- 229910052786 argon Inorganic materials 0.000 description 1
- 238000005219 brazing Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 229910001220 stainless steel Inorganic materials 0.000 description 1
- 239000010935 stainless steel Substances 0.000 description 1
Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/78—Other construction of jet pipes
- F02K1/80—Couplings or connections
-
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/78—Other construction of jet pipes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/78—Other construction of jet pipes
- F02K1/80—Couplings or connections
- F02K1/805—Sealing devices therefor, e.g. for movable parts of jet pipes or nozzle flaps
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The utility model provides a be suitable for two duct turbofan engine's tail nozzle structure, relates to aeroengine technical field for reduce the degree of difficulty that the tail nozzle is stably connected on two duct engines. The utility model provides a tail jet tube structure that is suitable for two duct turbofan engine, includes interior awl, well cartridge receiver and outer cartridge receiver that set gradually from inside to outside, interior awl with be equipped with interior duct between the well cartridge receiver, well cartridge receiver with be equipped with outer duct between the outer cartridge receiver, characterized by, two at least linking bridge have been linked firmly on the interior awl, each linking bridge encircles the circumference distribution of interior awl, the outer end of linking bridge links firmly on the outer cartridge receiver, well cartridge receiver links firmly on the linking bridge, be equipped with flange dish spare on the well cartridge receiver, flange dish spare detachably connects on the stator of engine.
Description
Technical Field
The invention relates to the technical field of aero-engines, in particular to a tail nozzle structure suitable for a double-duct turbofan engine.
Background
With the development of aviation industry and the requirement of military combat missions, the demand of microminiature turbofan engines is more and more. In view of the requirements of low cost and high reliability, many parts of the miniature turbofan engine cannot simply follow the structure of the large turbofan engine, and appropriate improvement or innovation is needed. Among them is the design of the jet nozzle.
The existing double-duct turbofan engine comprises an inner cone, a middle casing and an outer casing which are sequentially arranged from inside to outside, wherein an inner duct is arranged between the inner cone and the middle casing, and an outer duct is arranged between the middle casing and the outer casing. The structure is characterized in that the inner cone is fixedly connected with a fixing piece in an engine through a connecting piece, the middle casing is fixedly connected with an engine stator through a flange plate, the outer casing is fixedly connected with the outer casing of the engine through the flange plate, and no connecting piece is arranged between the middle casing and the outer casing. This also increases the difficulty of the jet nozzle connection. Meanwhile, the above connection scheme in the prior art also enables all loads of the outer casing to act on the area between the outer casing and the engine outer casing, and the area needs to be provided with a sealing element, so that the sealing abrasion and the pressure loss speed of the area are increased.
Disclosure of Invention
The invention aims to provide a tail spray pipe structure suitable for a double-duct turbofan engine, which is used for reducing the difficulty of stable connection of the tail spray pipe on the double-duct engine.
The technical scheme adopted by the invention for solving the technical problems is as follows:
the utility model provides a tail jet tube structure that is suitable for two duct turbofan engine, includes interior awl, well cartridge receiver and outer cartridge receiver that set gradually from inside to outside, interior awl with be equipped with interior duct between the well cartridge receiver, well cartridge receiver with be equipped with outer duct between the outer cartridge receiver, link firmly two at least linking bridge on the interior awl, each linking bridge encircles the circumference distribution of interior awl, the outer end of linking bridge links firmly on the outer cartridge receiver, well cartridge receiver links firmly on the linking bridge, be equipped with flange dish spare on the well cartridge receiver, flange dish spare detachably connects on the stator of engine.
The beneficial effects are that: the connecting support is used for fixedly connecting the inner cone, the middle casing and the outer casing together, the flange plate part is fixedly connected with the stator, the outer casing is supported and fixed, the stress at the joint of the outer casing and the outer casing of the engine can be greatly reduced, the design and processing cost is favorably reduced, the sealing structure between the outer casing and the outer casing of the engine is favorably protected, and the service life is favorably prolonged. Because the stator is a structural member, the additional stress caused by the indirect fixed connection of the outer casing is far less than the surplus of the bearing capacity of the stator, and the stator structure does not need to be adjusted. The surplus space can completely use the stress distribution of the position. Meanwhile, the inner cone plays a role of airflow diversion and also plays a role of an internal support piece, namely, plays a role of structural support and bearing for the middle casing and the outer casing, avoids deformation of the middle casing and the outer casing, and keeps the accuracy of the volumes of the inner duct and the outer duct.
Further, the inner end of the connecting bracket is welded on the inner cone.
The beneficial effects are that: the stability of the structure is favorably maintained.
Furthermore, each connecting support is welded with the middle case.
The beneficial effects are that: the stability of the structure is favorably maintained.
Further, the outer end of the connecting bracket is detachably connected to the outer casing through a screw member.
The beneficial effects are that: the disassembly, assembly and maintenance work of the invention are convenient.
Furthermore, a screw seat for penetrating and sleeving the screw piece is arranged on the outer casing, and a threaded hole matched with the screw piece is formed in the outer end of the connecting support.
The beneficial effects are that: the connection work of the screw piece is convenient.
Further, the screw seat is welded on the outer casing.
The beneficial effects are that: the screw seat can be conveniently machined on the screw seat.
Furthermore, a threaded hole seat is embedded in the connecting support, and a threaded hole matched with the screw piece is formed in the threaded hole seat.
The beneficial effects are that: the processing work of screw hole is convenient for.
Furthermore, a diversion angle is arranged on the front side of the connecting bracket and is arranged forwards.
The beneficial effects are that: the resistance of the airflow is reduced, and the efficiency of the engine is improved.
Drawings
FIG. 1 is a schematic diagram of an embodiment of the present invention;
fig. 2 is an enlarged view of a portion a in fig. 1;
FIG. 3 is a perspective view of an embodiment of the inner cone, the middle case, and the connecting bracket;
FIG. 4 is a schematic front view of FIG. 3;
FIG. 5 is a schematic cross-sectional view taken along line B-B of FIG. 4;
in the figure: 1 stator, 11 rotating shafts, 12 turbofan, 13 engine outer box, 2 inner cone, 3 middle box, 31 flange plate piece, 4 outer box, 41 screw piece, 42 screw seat, 5 inner duct, 6 outer duct, 7 connecting bracket, 71 threaded hole seat and 72 flow guide angle.
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, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, are within the scope of the present invention.
As shown in fig. 1 and 3, fig. 1 and 3 represent two alternative variants for the arrangement of the threaded bore for cooperation with the screw member 41. Fig. 1 and 3 show two different distribution schemes for the distribution of the hole positions for the bolts on the flange plate 31.
As shown in fig. 1 to 5, the exhaust nozzle structure suitable for the dual-bypass turbofan engine comprises a stator 1 and a rotating shaft 11 rotatably arranged relative to the stator 1, wherein the rotating shaft 11 is provided with a turbofan 12. A tail nozzle structure suitable for a double-duct turbofan engine comprises an inner cone 2, a middle engine box 3 and an outer engine box 4 which are sequentially arranged from inside to outside, wherein the inner cone 2 is defined to be arranged close to the rear relative to a rotating shaft 11. An inner duct 5 is arranged between the inner cone 2 and the middle casing 3, an outer duct 6 is arranged between the middle casing 3 and the outer casing 4, at least two connecting supports 7 are fixedly connected to the inner cone 2, each connecting support 7 is distributed around the circumferential direction of the inner cone 2, the outer end of each connecting support 7 is fixedly connected to the outer casing 4, the middle casing 3 is fixedly connected to the connecting supports 7, a flange plate 31 is arranged on the middle casing 3, and the flange plate 31 is detachably connected to the stator 1 of the engine. The inner end of the connecting bracket 7 is welded on the inner cone 2. The connecting brackets 7 are respectively welded with the middle case 3. The outer end of the connecting bracket 7 is detachably connected to the outer case 4 by a screw member 41. The inner cone 2, the middle case 3, the outer case 4 and the connecting bracket 7 can be made of stainless steel S304, S310 and the like, and the welding can be brazing, argon arc welding and the like. The preferred number of connecting brackets 7 is three or four. The outer casing 4 is connected with the outer casing of the engine through a bolt group, and is provided with sealing.
1-5, an assembly of an exhaust nozzle structure suitable for a dual ducted turbofan engine is as follows: the inner cone 2, the middle engine box 2 and the connecting bracket 7 are fixedly connected through welding to form an integrated structure → then the flange plate piece 7 is fixedly connected on the stator 1 through bolts → the outer engine box 4 is fixedly connected to the outer end of the connecting bracket 7 → the outer engine box 4 is connected with the outer engine box 13.
As shown in fig. 1 to 5, the beneficial effects of the present invention are: the inner cone 2, the middle case 3 and the outer case 4 are fixedly connected together through the connecting support 7, the flange plate 31 is fixedly connected with the stator 1, the outer case 4 is supported and fixed, stress at the joint of the outer case 4 and the outer case 13 of the engine can be greatly reduced, design and processing cost reduction is facilitated, a sealing structure between the outer case 4 and the outer case 13 of the engine can be protected, and service life is prolonged. Because the stator 1 is a structural member, the additional stress caused by the indirect fixed connection of the outer casing 4 is far less than the surplus of the bearing capacity of the stator, and therefore, the stator structure does not need to be adjusted. The surplus space can completely use the stress distribution of the position. Meanwhile, the inner cone 2 plays a role of an air flow guide and also plays a role of an internal support piece, namely, plays a role of a structural support bearing for the middle casing 3 and the outer casing 4, avoids deformation of the middle casing 3 and the outer casing 4, and keeps the accuracy of the volumes of the inner duct and the outer duct.
As shown in fig. 1 and 2, the outer casing 4 is provided with a screw seat 42 for receiving a screw member 41 therethrough, and the outer end of the connecting bracket 7 is provided with a screw hole for engaging with the screw member 41. The screw seat 42 is welded to the outer case 4. A threaded hole seat 71 is embedded in the connecting bracket 7, and a threaded hole for matching with the screw member 41 is formed in the threaded hole seat 71.
As shown in fig. 3-5, for the technical solution of the threaded hole, the threaded hole may be directly formed at the end of the connecting bracket.
As shown in fig. 3, a diversion angle 72 is arranged at the front side of the connecting bracket 7, and the diversion angle 72 is arranged forward, so that the resistance to the air flow is favorably reduced, and the working efficiency of the engine is further ensured.
In this embodiment, the connecting bracket has a solid structure. Besides, the connecting bracket can also adopt a hollow structure. The hollow connecting bracket can be processed by sheet metal through sheet metal plates, so that the overall quality of the airplane can be reduced.
Claims (8)
1. The utility model provides a tail jet tube structure that is suitable for two duct turbofan engine, includes interior awl, well cartridge receiver and outer cartridge receiver that set gradually from inside to outside, interior awl with be equipped with interior duct between the well cartridge receiver, well cartridge receiver with be equipped with outer duct between the outer cartridge receiver, characterized by, two at least linking bridge have been linked firmly on the interior awl, each linking bridge encircles the circumference distribution of interior awl, the outer end of linking bridge links firmly on the outer cartridge receiver, well cartridge receiver links firmly on the linking bridge, be equipped with flange dish spare on the well cartridge receiver, flange dish spare detachably connects on the stator of engine.
2. The jet nozzle arrangement adapted for a dual ducted turbofan engine of claim 1 wherein the inner end of said attachment bracket is welded to said inner cone.
3. The jet nozzle arrangement adapted for a dual ducted turbofan engine of claim 1 wherein each of said attachment brackets is welded to said center case.
4. The jet nozzle arrangement adapted for a dual ducted turbofan engine of claim 1 wherein the outer end of said attachment bracket is removably attached to said outer case by screw members.
5. The nozzle tip structure of claim 4 wherein said outer casing has screw seats for receiving said screw members, and said connecting bracket has threaded holes at its outer end for engaging said screw members.
6. The nozzle tip arrangement for a dual ducted turbofan engine of claim 5 wherein the screw bosses are welded to the outer case.
7. The exhaust nozzle structure for a dual-ducted turbofan engine according to claim 5, wherein a threaded socket is embedded in the connection bracket, the threaded socket having a threaded hole for mating with the screw member.
8. The exhaust nozzle structure for a dual-ducted turbofan engine according to claim 1 wherein the forward side of the linking struts is provided with a diversion angle that is disposed forward.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210910634.5A CN115355103A (en) | 2022-07-29 | 2022-07-29 | Tail jet pipe structure suitable for double-duct turbofan engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210910634.5A CN115355103A (en) | 2022-07-29 | 2022-07-29 | Tail jet pipe structure suitable for double-duct turbofan engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115355103A true CN115355103A (en) | 2022-11-18 |
Family
ID=84032534
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210910634.5A Pending CN115355103A (en) | 2022-07-29 | 2022-07-29 | Tail jet pipe structure suitable for double-duct turbofan engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115355103A (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1069507A (en) * | 1966-02-18 | 1967-05-17 | Rolls Royce | Annular flow duct |
| JPH0640303U (en) * | 1992-10-29 | 1994-05-27 | 石川島播磨重工業株式会社 | Exhaust duct strut structure |
| US20060010852A1 (en) * | 2004-07-16 | 2006-01-19 | Pratt & Whitney Canada Corp. | Turbine exhaust case and method of making |
| CN104819016A (en) * | 2015-05-05 | 2015-08-05 | 中国航空动力机械研究所 | Turbine rear support bearing seat, cooling method and turbine fan engine |
| CN111963263A (en) * | 2020-08-18 | 2020-11-20 | 中国航发沈阳发动机研究所 | Connecting type engine turbine force-bearing frame |
| CN114165301A (en) * | 2021-12-14 | 2022-03-11 | 中国航发沈阳发动机研究所 | Engine stator stable connection structure and method |
-
2022
- 2022-07-29 CN CN202210910634.5A patent/CN115355103A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1069507A (en) * | 1966-02-18 | 1967-05-17 | Rolls Royce | Annular flow duct |
| JPH0640303U (en) * | 1992-10-29 | 1994-05-27 | 石川島播磨重工業株式会社 | Exhaust duct strut structure |
| US20060010852A1 (en) * | 2004-07-16 | 2006-01-19 | Pratt & Whitney Canada Corp. | Turbine exhaust case and method of making |
| CN104819016A (en) * | 2015-05-05 | 2015-08-05 | 中国航空动力机械研究所 | Turbine rear support bearing seat, cooling method and turbine fan engine |
| CN111963263A (en) * | 2020-08-18 | 2020-11-20 | 中国航发沈阳发动机研究所 | Connecting type engine turbine force-bearing frame |
| CN114165301A (en) * | 2021-12-14 | 2022-03-11 | 中国航发沈阳发动机研究所 | Engine stator stable connection structure and method |
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