CN104214008B - A kind of novel tail cone - Google Patents
A kind of novel tail cone Download PDFInfo
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- CN104214008B CN104214008B CN201410249881.0A CN201410249881A CN104214008B CN 104214008 B CN104214008 B CN 104214008B CN 201410249881 A CN201410249881 A CN 201410249881A CN 104214008 B CN104214008 B CN 104214008B
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Abstract
A kind of novel tail cone, belong to aeroengine tail cone development field, it is characterized in that: this cone comprise mounting edge (1), outer wall leading portion (2), circle turn the compositions such as elliptical cone (3), intensity stiffening ring (4), axle center ventilation supporting base (5), mounting edge inside support ring (6); Meanwhile, the outer profile face of this cone structure is non-axis symmetry shape face, and cone-shape face is by the shape face of circular cross-section to oval cross section transition; This asymmetric cone structure can adapt to the demand of offset nozzle, ensures that it has good pneumatic effect.The novel tail cone of one provided by the invention, advantage is: the demand that can adapt to offset nozzle, there is good aerodynamic characteristic and lower infrared signature, this cone has good structural strength simultaneously, this conoid is mainly used in motor taper designs, has good application prospect.
Description
Technical field
The present invention relates to aeroengine tail cone development field, belong to the tail cone design field of aeroengine, be specifically related to the improvement of a kind of tail bone design.
Background technique
Available engine tail cone is all the tail cone of axial symmery shape, this kind of tail cone can meet the demand of traditional axisymmetric nozzle, but along with the raising that stealth requires, there is the jet pipe that offset nozzle etc. is new, this just requires to redesign the new asymmetric tail cone of the new model mated with it, this kind of tail cone can regulate the aerodynamic loss reduced with offset nozzle, regulate high temperature gas flow and the distribution situation of low-temperature airflow in cross section, significant to the aeroperformance realizing the vent systems be made up of asymmetric tail cone and offset nozzle, the infrared signature of gas flow can be reduced simultaneously.
Summary of the invention
The object of the present invention is to provide a kind of novel tail cone, this kind of tail cone can regulate the aerodynamic loss reduced with offset nozzle, regulates high temperature gas flow and the distribution situation of low-temperature airflow in cross section.This tail cone has important function to realizing mating very well with offset nozzle stream face, by the design of this tail cone, can ensure, together with offset nozzle, there is less aerodynamic loss, simultaneously this tail cone to change cross section high temperature gas flow and low-temperature airflow significant in the distribution situation in cross section.
Technological scheme of the present invention is: a kind of novel tail cone, is characterized in that: this cone comprise mounting edge 1, outer wall leading portion 2, circle turn elliptical cone 3, intensity stiffening ring 4, axle center ventilation supporting base 5 and mounting edge inside support ring 6; The cone-shape face that circle turns elliptical cone 3 is by the shape face of circular cross-section to oval cross section transition, and its asymmetrical cone-shape region feature, can be applicable to the demand of offset nozzle, and circle turns elliptical cone 3 with outer wall leading portion 2 by being welded to connect; The outer profile face of this tail cone is non-axis symmetry shape face, and cone-shape face is by the shape face of circular cross-section to oval cross section transition.
Described mounting edge 1 is the bindiny mechanism connecting cone and motor, and be the stress members that subject whole cone, mounting edge 1 is cirque structure part simultaneously.
Described outer wall leading portion 2 is ring sheet metal part, and connection limit 1 turns elliptical cone 3 with circle, and outer wall leading portion 2 and mounting edge 1 are by being welded to connect.
Described intensity stiffening ring 4 turns elliptical cone 3 inwall stage casing by being welded to connect at circle, and the profile of described intensity stiffening ring 4 is consistent with the cooperation cross section that circle turns elliptical cone 3.
Described axle center ventilation supporting base 5 is hollow structure, and to turn elliptical cone 3 inner wall of end consistent for appearance profile and circle, and is welded on to justify and turns elliptical cone 3 port inner wall.
Described mounting edge inside support ring 6 is loop configuration, and weld with mounting edge 1 and outer wall leading portion 2 respectively, three forms cavity.
The novel tail cone of one provided by the invention, advantage is: the demand that can adapt to offset nozzle, there is good aerodynamic characteristic and lower infrared signature, this cone has good structural strength simultaneously, this conoid is mainly used in motor taper designs, has good application prospect.
Accompanying drawing explanation
Fig. 1 asymmetric cone structure composition schematic diagram;
Fig. 2 mounting edge;
Fig. 3 outer wall leading portion;
Fig. 4 circle turns elliptical cone;
Fig. 5 intensity stiffening ring;
Fig. 6 axle center ventilation supporting base;
Fig. 7 mounting edge inside support ring.
Embodiment
Embodiment 1
A kind of novel tail cone, is characterized in that: this jet pipe comprises mounting edge 1, outer wall leading portion 2, circle turn the compositions such as elliptical cone 3, intensity stiffening ring 4, axle center ventilation supporting base 5, mounting edge inside support ring 6.
1) mounting edge 1 is the bindiny mechanism connecting cone and motor, and be the stress members that subject whole cone, mounting edge 1 is tubular structural member simultaneously.
2) outer wall leading portion 2 connection limit and cone outer wall shape face, outer wall leading portion 2 and mounting edge 1 are by being welded to connect.
3) circle turns the cone-shape face of elliptical cone 3 is by the shape face of circular cross-section to oval cross section transition, and its asymmetrical cone-shape region feature, can be applicable to the demand of offset nozzle, and circle turns elliptical cone 3 with outer wall leading portion 2 by being welded to connect;
4) intensity stiffening ring 4 keeps circle to turn the indeformable parts of elliptical cone 3, and intensity stiffening ring 4 turns elliptical cone 3 by being welded to connect with circle;
5) axle center ventilation supporting base 5 is one of vitals connecting axle center ventilation duct, and axle center ventilation supporting base 5 turns elliptical cone 3 by being welded to connect with circle.
Claims (6)
1. a novel tail cone, comprise mounting edge (1), it is characterized in that: also comprise outer wall leading portion (2), circle turns elliptical cone (3), intensity stiffening ring (4), axle center ventilation supporting base (5) and mounting edge inside support ring (6); The cone-shape face that circle turns elliptical cone (3) is by the shape face of circular cross-section to oval cross section transition, its asymmetrical cone-shape region feature, can be applicable to the demand of offset nozzle, circle turns elliptical cone (3) with outer wall leading portion (2) by being welded to connect; The outer profile face of this tail cone is non-axis symmetry shape face.
2. the novel tail cone of one according to claim 1, it is characterized in that: described mounting edge (1) is the bindiny mechanism connecting cone and motor, be the stress members that subject whole cone, mounting edge (1) is cirque structure part simultaneously.
3. the novel tail cone of one according to claim 1, it is characterized in that: described outer wall leading portion (2) is ring sheet metal part, connection limit (1) turns elliptical cone (3) with circle, and outer wall leading portion (2) and mounting edge (1) are by being welded to connect.
4. the novel tail cone of one according to claim 1, it is characterized in that: described intensity stiffening ring (4) turns elliptical cone (3) inwall stage casing by being welded to connect at circle, the profile of described intensity stiffening ring (4) is consistent with the cooperation cross section that circle turns elliptical cone (3).
5. the novel tail cone of one according to claim 1, it is characterized in that: described axle center ventilation supporting base (5) is hollow structure, to turn elliptical cone (3) inner wall of end consistent for appearance profile and circle, and be welded on to justify and turn elliptical cone (3) port inner wall.
6. the novel tail cone of one according to claim 1, is characterized in that: described mounting edge inside support ring (6) is loop configuration, and weld with mounting edge (1) and outer wall leading portion (2) respectively, three forms cavity.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410249881.0A CN104214008B (en) | 2014-06-06 | 2014-06-06 | A kind of novel tail cone |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410249881.0A CN104214008B (en) | 2014-06-06 | 2014-06-06 | A kind of novel tail cone |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104214008A CN104214008A (en) | 2014-12-17 |
| CN104214008B true CN104214008B (en) | 2016-03-09 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410249881.0A Active CN104214008B (en) | 2014-06-06 | 2014-06-06 | A kind of novel tail cone |
Country Status (1)
| Country | Link |
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| CN (1) | CN104214008B (en) |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104832317B (en) * | 2015-04-02 | 2017-03-01 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of device controlling inner cone amount of air entrainment |
| CN109372653A (en) * | 2018-12-13 | 2019-02-22 | 中国航发沈阳发动机研究所 | A kind of fanjet noise-reducing exhaust component |
| CN112282938B (en) * | 2020-10-28 | 2021-05-28 | 上海尚实能源科技有限公司 | Centerbody assembly for a gas turbine engine |
| CN114215656A (en) * | 2021-12-01 | 2022-03-22 | 中国航发沈阳发动机研究所 | Enhanced air cooling center cone |
| CN114233514A (en) * | 2021-12-01 | 2022-03-25 | 中国航发沈阳发动机研究所 | Forced convection air cooling center cone |
| CN115614173B (en) * | 2022-12-19 | 2023-02-28 | 中国航发沈阳发动机研究所 | Radial overlap joint axial grafting inner cone installation edge structure |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102285457A (en) * | 2010-04-26 | 2011-12-21 | 空中客车西班牙运营有限责任公司 | Configuration of a rear fuselage tail cone of an aircraft with an auxiliary power unit |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7950236B2 (en) * | 2006-09-11 | 2011-05-31 | Pratt & Whitney Canada Corp. | Exhaust duct and tail cone attachment of aircraft engines |
| EP2074315A1 (en) * | 2006-10-12 | 2009-07-01 | United Technologies Corporation | Controlling ice buildup on aircraft engine and nacelle static and rotating components |
| US8341935B2 (en) * | 2007-06-05 | 2013-01-01 | The Boeing Company | Internal mixing of a portion of fan exhaust flow and full core exhaust flow in aircraft turbofan engines |
| US9003811B2 (en) * | 2011-11-28 | 2015-04-14 | Pratt & Whitney Canada Corp. | Support for electric machine in a turbine engine |
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2014
- 2014-06-06 CN CN201410249881.0A patent/CN104214008B/en active Active
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102285457A (en) * | 2010-04-26 | 2011-12-21 | 空中客车西班牙运营有限责任公司 | Configuration of a rear fuselage tail cone of an aircraft with an auxiliary power unit |
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| Publication number | Publication date |
|---|---|
| CN104214008A (en) | 2014-12-17 |
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Inventor after: Deng Hongwei Inventor after: Liu Chao Inventor before: Deng Hongwei |
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| CB03 | Change of inventor or designer information |