CN112727634B - Rectangular cross-section spray pipe - Google Patents

Rectangular cross-section spray pipe Download PDF

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Publication number
CN112727634B
CN112727634B CN202011439429.2A CN202011439429A CN112727634B CN 112727634 B CN112727634 B CN 112727634B CN 202011439429 A CN202011439429 A CN 202011439429A CN 112727634 B CN112727634 B CN 112727634B
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CN
China
Prior art keywords
spray pipe
pipe body
metal cover
outlet
nozzle
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CN202011439429.2A
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Chinese (zh)
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CN112727634A (en
Inventor
晋晓伟
周建平
张蒙正
闫联生
张�浩
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Xian Aerospace Propulsion Institute
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Xian Aerospace Propulsion Institute
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Priority to CN202011439429.2A priority Critical patent/CN112727634B/en
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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
    • 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
    • F02K1/82—Jet pipe walls, e.g. liners
    • F02K1/822—Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infrared radiation suppressors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
    • F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
    • F02K7/14—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines with external combustion, e.g. scram-jet engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
    • F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
    • F02K7/18—Composite ram-jet/rocket engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/97—Rocket nozzles
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Thermal Insulation (AREA)

Abstract

The invention discloses a rectangular section spray pipe, wherein the spray pipe comprises: the spray pipe comprises a spray pipe body, a circumferential reinforcing rib, a metal cover, a heat insulation plate and a heat insulation felt; the annular reinforcing ribs are arranged on the outer surface of the rear area of the spray pipe body in a surrounding mode, wherein the spray pipe body is made of carbon/carbon-silicon carbide composite materials, and the spray pipe body is a rectangular section flow channel; the metal cover is arranged on the outer surface of the inlet area of the spray pipe body; the thermal insulation plate is coated on the outer wall of the spray pipe body; and the heat insulation felt is filled between the outer side of the outlet of the spray pipe body and the partition frame of the aircraft body. The rectangular section spray pipe disclosed by the invention has the characteristics of high temperature resistance, high heat flow gas resistance, light weight and the like.

Description

Rectangular cross-section spray pipe
Technical Field
The invention belongs to the technical field of hypersonic aircrafts, and particularly relates to a rectangular-section spray pipe.
Background
The two-dimensional rectangular section spray pipe has the advantages of easy flow channel adjustment of the aircraft and integration with the aircraft, and is generally applied to hypersonic aircrafts.
The jet pipe is used as a main thrust part of a scramjet engine and a rocket-based combined cycle engine, and special requirements such as structural weight reduction, aircraft cabin body temperature limitation, aircraft structural space constraint and the like need to be met except for the problems of bearing high temperature, high heat flow, strong vibration and the like faced by other types of jet pipes.
In order to realize the reliable work of the engine, the engine is suitable for the application of a super aircraft and a missile which take a super-combustion ramjet engine and a rocket-based combined cycle engine as power. Needs to solve the following problems: 1) a lightweight high-temperature resistant structure design technology; 2) a light high-efficiency thermal protection technology; 3) large vibration, shock isolation techniques. There is often a conflict between these requirements in the structural design.
Taking a rocket-based combined cycle power aircraft as an example, the structural design of the nozzle of the rocket-based combined cycle power aircraft faces the following contradiction.
On one hand, for the rocket-based combined cycle engine jet pipe, under the action of two high-temperature fuel gas jet flows, the highest temperature of the wall surface is close to 2000K and exceeds the melting point of a common metal material. On the other hand, according to the requirements of normal working environment of other components in the aircraft cabin body, the temperature of the outer wall of the spray pipe is not more than 150 ℃.
On the other hand, the jet pipe is positioned at the tail part of the aircraft, the rear end of the jet pipe is often provided with a solid booster, and the vibration environment of the jet pipe is most severe and the structural strength of the jet pipe must be high enough at the time of boosting ignition and separation and the time of normal operation of an engine. On the other hand, the aircraft is subject to the requirements of centre of gravity configuration and overall mass control, and the nozzles need to be as lightweight as possible.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the jet pipe is light in structure, high-temperature resistant, efficient and heat-insulating, and meets the requirements of matching aircraft shapes, structure weight reduction, high-temperature gas resistance and the like of super aircrafts and missiles which take a super-combustion ramjet engine and a rocket-based combined cycle engine as power.
In order to solve the technical problem, the invention discloses a rectangular section spray pipe, wherein the spray pipe comprises: the spray pipe comprises a spray pipe body, a circumferential reinforcing rib, a metal cover, a heat insulation plate and a heat insulation felt; the annular reinforcing ribs are arranged on the outer surface of the rear area of the spray pipe body in a surrounding mode, wherein the spray pipe body is made of carbon/carbon-silicon carbide composite materials, and the spray pipe body is a rectangular section flow channel; the metal cover is arranged on the outer surface of the inlet area of the spray pipe body; the thermal insulation plate is coated on the outer wall of the spray pipe body; and the heat insulation felt is filled between the outer side of the outlet of the pipe spraying body and a partition frame of an aircraft body.
Preferably, four corners of the rectangular section of the nozzle body are rounded;
the rectangular cross-sectional area gradually increases from the spout body inlet to the spout body outlet;
the radius of the four corner fillets of the rectangular section is gradually increased from the inlet of the nozzle body to the outlet of the nozzle body.
Preferably, the inlet of the spray pipe body is of a flange structure, the outlet of the spray pipe body is of a straight structure, and the spray pipe body is of a variable wall thickness structure.
Preferably, the wall thickness of the nozzle body except the flange and the outlet straight section is gradually reduced from the inlet of the nozzle body to the outlet of the nozzle body.
Preferably, the wall thickness of the nozzle body is gradually reduced from 12mm to 6 mm.
Preferably, the circumferential reinforcing ribs are made of carbon fiber/phenolic aldehyde composite materials.
Preferably, the metal cover is made of high-temperature alloy.
Preferably, the metal cover is a topological appearance structure; reinforcing ribs are arranged at the root part of a flange at the inlet of the metal cover, four corners of the metal cover are protruded, and the middle part is recessed; the wall thickness of the metal cover is gradually reduced from the inlet of the metal cover to the outlet of the metal cover.
Preferably, the thermal insulation board is a nano-porous aerogel thermal insulation composite material.
Preferably, the heat insulation felt is an aluminum silicate fiber base material.
According to the rectangular-section spray pipe provided by the embodiment of the application, on the first hand, the spray pipe body is made of carbon/carbon-silicon carbide composite materials, and has the characteristics of high temperature resistance, high heat flow resistance and light weight; in the second aspect, the annular reinforcing ribs are arranged at the outlet of the spray pipe body, so that the rigidity of the outlet of the spray pipe can be improved, and the internal pressure bearing capacity can be improved; in the third aspect, the outer wall of the spray pipe body is coated with a heat insulation plate, so that the external temperature of the spray pipe is reduced to the bearable range of aircraft equipment; the metal cover is arranged at the inlet of the spray pipe body, and the heat insulation felt is filled between the outlet end of the spray pipe and the aircraft cabin body, so that the vibration damping device has a good vibration damping effect.
Drawings
Fig. 1 is a schematic structural diagram of a rectangular cross-section nozzle according to an embodiment of the present invention.
Detailed Description
The present invention will be described in detail below with reference to specific embodiments and with reference to the attached drawings. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
Fig. 1 is a schematic structural diagram of a rectangular-section nozzle provided in an embodiment of the present invention.
The rectangular cross-section nozzle of the embodiment of the invention comprises: the spray pipe comprises a spray pipe body 1, a circumferential reinforcing rib 2, a heat insulation plate 3, a metal cover 4 and a heat insulation felt 5; the annular reinforcing ribs 2 are arranged on the outer surface of the rear area of the spray pipe body 1 in a surrounding mode; the metal cover 4 is arranged on the outer surface of the inlet area of the nozzle body 1; the thermal insulation board 3 is coated on the outer wall of the spray pipe body 1; and a heat insulation felt is filled between the outer side of the outlet of the spray pipe body and the partition frame of the aircraft body.
The spray pipe body 1 is a flow channel with a rectangular cross section; the nozzle body is made of carbon/carbon-silicon carbide composite material. The nozzle body is made of carbon/carbon-silicon carbide composite materials, and can bear a high-temperature oxygen-containing gas environment close to 2000K. The rectangular section runner can realize the efficient space matching of the spray pipe and the engine body.
In an alternative embodiment, the rectangular cross-section of the nozzle body is treated with four corner rounding; the rectangular cross-sectional area is gradually increased from the inlet of the nozzle body to the outlet of the nozzle body; the radiuses of the four corner fillets of the rectangular section are gradually increased from the inlet of the nozzle body to the outlet of the nozzle body.
The quasi-rectangular cross section with the circular angle is capable of effectively reducing structural stress concentration of four corners of the spray pipe on the premise of not changing aerodynamic performance of the flow channel. And the gradually increased fillets are adopted from the inlet of the rectangular nozzle body to the outlet of the nozzle body, so that the requirements of integration with an aircraft and structural deformation resistance can be met.
In an alternative embodiment, the nozzle body inlet is of a flanged configuration, the nozzle body outlet is of a straight configuration, and the nozzle body is of a variable wall thickness configuration.
The spray pipe body adopts a variable wall thickness structure, adapts to the working environment that the pressure inlet is reduced to the outlet in the spray pipe, and is favorable for forward adjustment of the gravity center of the spray pipe, and the bearing capacity of the flange at the inlet of the spray pipe is improved. The inlet end of the spray pipe body is of a flange structure, so that the spray pipe is connected with the combustion chamber, and the outlet of the spray pipe body is a straight section, so that the spray pipe body is matched with an aircraft cabin body. The part of the inlet of the spray pipe, which is close to the flange, is reinforced by the metal cover, so that the stress concentration at the root part of the flange of the composite spray pipe body can be reduced, and the overload, vibration and impact bearing capacity of the spray pipe is improved.
In an alternative embodiment, the wall thickness of the spout body, excluding the flange and outlet straight section, tapers from the spout body inlet to the spout body outlet. Optionally, the wall thickness of the nozzle body is gradually reduced from 12mm to 6 mm.
In an alternative embodiment, the circumferential reinforcing ribs are carbon fiber/phenolic composite material.
The carbon fiber/phenolic aldehyde composite material annular reinforcing ribs are arranged in the rear area of the spray pipe, so that the strength and rigidity of the rear part of the spray pipe body can be improved on the premise of not increasing the weight remarkably, the bearing capacity of the structure is improved, and the structural deformation is reduced. The reinforcing ribs are distributed at intervals, and the interval distance is approximately equivalent to the width dimension of the reinforcing ribs.
In an alternative embodiment, the metal shield is a high temperature alloy material; the metal cover is in a topological shape structure; reinforcing ribs are arranged at the root part of a flange at the inlet of the metal cover, four corners of the metal cover are protruded, and the middle part is recessed; the wall thickness of the metal cover is gradually reduced from the inlet of the metal cover to the outlet of the metal cover.
The metal cover adopts the variable wall thickness and the topological shape according to the configuration and the force-heat environment of the spray pipe body, and meets the requirements of vibration reduction and deformation matching of the spray pipe.
In an alternative embodiment, the insulating panel is a nanoporous aerogel insulation composite.
The thermal insulation board of the nanometer porous aerogel thermal insulation composite material is coated outside the spray pipe body, so that the temperature of the outer wall of the spray pipe can be controlled below 150 ℃, and the ambient temperature in the aircraft cabin can be ensured to meet the requirement of the working environment temperature of surrounding equipment.
In an alternative embodiment, the insulation blanket is an aluminum silicate fiber matrix material.
Under the spray pipe assembled state, the inlet is connected through the combustion chamber and is realized fixing, the outlet is not connected by force, and the heat insulation felt is filled between the outer side of the straight section of the outlet and the aircraft body partition frame. Under the working state, the outlet of the spray pipe is high-temperature fuel gas, and the spray pipe bears large-magnitude vibration and impact. The heat insulation felt made of the aluminum silicate fiber base material has a good heat insulation effect and can insulate high-temperature fuel gas at the outlet of the spray pipe; meanwhile, the heat insulation felt has high compressibility, and can effectively isolate fuel gas at the outlet of the spray pipe and reduce vibration and impact magnitude.
According to the rectangular-section spray pipe provided by the embodiment of the invention, on the first hand, the spray pipe body is made of the carbon/carbon-silicon carbide composite material, and has the characteristics of high temperature resistance, high heat flow resistance and light weight; in the second aspect, the annular reinforcing rib is arranged at the outlet of the spray pipe body, so that the rigidity of the outlet of the spray pipe can be improved, and the internal pressure bearing capacity of the spray pipe can be improved; in the third aspect, the outer wall of the spray pipe body is coated with a heat insulation plate, so that the temperature outside the spray pipe is reduced to a bearable range of aircraft equipment; the metal cover is arranged at the inlet of the spray pipe body, and the heat insulation felt is filled between the outlet end of the spray pipe and the aircraft cabin body, so that the vibration damping device has a good vibration damping effect.
The following description is given by taking specific examples to illustrate the arrangement of the nozzle for the rocket-based combined-cycle engine:
(1) determining that an inner runner of the spray pipe is a two-dimensional expansion profile according to a design result of the profile of the engine, wherein the height H of an inlet of the inner runner is 150mm, and the width W of the inlet of the inner runner is 230 mm; the height of the outlet is 490mm, and the width W is 360 mm; the four ridge lines of the inner flow passage are in variable diameter and are rounded, and the radius of a fillet from the inlet to the outlet is changed from R8 to R15;
(2) the nozzle body is made of carbon/carbon-silicon carbide ceramic matrix composite, the inlet is designed into a flange according to installation requirements, the outlet is designed into a straight section according to aircraft installation requirements, the main body part is of a variable wall thickness structure, and the wall thickness of the nozzle body is reduced to 6mm from the inlet to the outlet.
(3) The rear part of the nozzle body adopts the carbon fiber/phenolic aldehyde composite material circumferential reinforcing ribs, the number of the reinforcing ribs is 4, the width of the reinforcing ribs at the straight section of the outlet is equivalent to that of the straight section, the width of the other 3 reinforcing ribs is 50mm, the interval is 50mm, and the thickness of the reinforcing ribs is 5 mm;
(4) and a metal cover is arranged near the inlet flange of the spray pipe, and the metal cover is made of high-temperature alloy materials. The inlet section of the metal cover is of a flange structure and is matched with the inlet flange interface of the spray pipe, and the root of the flange is provided with a reinforcing rib. The metal cover is of a topological appearance structure, the length of the metal cover is 120mm along the axial direction, the protruding lengths of four corners are 120mm, and the middle part is concave; the metal cover is of a variable-thickness structure, the thickness of the flange and the reinforcing rib is 4mm, the wall thickness of the wall surface of the main body is 3mm, and the outlet is transited to 0.4-0.5 mm;
(5) the thermal insulation board outside the spray pipe is made of a nano porous aerogel thermal insulation composite material, the thickness of the thermal insulation board is 12-15 mm, and the temperature of the outer wall can be ensured not to be higher than 150 ℃;
(6) and in the straight section of the spray pipe outlet, a heat insulation felt is filled between the outer side of the heat insulation plate and a partition frame of an aircraft body, the base material of the heat insulation felt is aluminum silicate fiber, and the initial installation compression amount of the heat insulation felt is 15% +/-5%.
The carbon/carbon-silicon carbide composite material spray pipe with the similar rectangular cross section, which is light in structure, suitable for large vibration and impact, high-temperature resistant, efficient and heat insulation, provided by the specific example meets the requirements of matching aircraft shapes, structure weight reduction, high-temperature gas resistance and large vibration environment, meeting the requirement of thermal environment in a cabin and the like of a super aircraft and a missile taking a rocket-based combined cycle engine as power.
It should be noted that the above description is only a preferred embodiment of the present invention, and it should be understood that various changes and modifications can be made by those skilled in the art without departing from the technical idea of the present invention, and these changes and modifications are included in the protection scope of the present invention.
The above description is only for the best mode of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention.
Those skilled in the art will appreciate that the details of the invention not described in detail in this specification are well within the skill of those in the art.

Claims (6)

1. A rectangular cross-section nozzle for a hypersonic aircraft, the nozzle comprising: the spray pipe comprises a spray pipe body, a circumferential reinforcing rib, a metal cover, a heat insulation plate and a heat insulation felt;
the annular reinforcing ribs are arranged on the outer surface of the rear area of the spray pipe body in a surrounding mode, wherein the spray pipe body is made of carbon/carbon-silicon carbide composite materials, and the spray pipe body is a rectangular section flow channel;
the metal cover is arranged on the outer surface of the inlet area of the spray pipe body;
the thermal insulation plate is coated on the outer wall of the spray pipe body;
the heat insulation felt is filled between the outer side of the outlet of the spray pipe body and a partition frame of an aircraft body;
four corners of the rectangular section of the nozzle body are rounded;
the rectangular cross-sectional area gradually increases from the spout body inlet to the spout body outlet;
the radius of the fillet at the four corners of the rectangular section is gradually increased from the inlet of the nozzle body to the outlet of the nozzle body;
the inlet of the spray pipe body is of a flange structure, the outlet of the spray pipe body is of a straight structure, and the spray pipe body is of a variable wall thickness structure;
the wall thickness of the spray pipe body except the flange and the outlet straight section is gradually reduced from the inlet of the spray pipe body to the outlet of the spray pipe body; wherein,
the metal cover is of a topological appearance structure;
reinforcing ribs are arranged at the root part of a flange at the inlet of the metal cover, four corners of the metal cover are protruded, and the middle part of the metal cover is sunken;
the wall thickness of the metal cover is gradually reduced from the inlet of the metal cover to the outlet of the metal cover.
2. The rectangular cross-section nozzle of a hypersonic aircraft as in claim 1, wherein: the wall thickness of the nozzle body is gradually reduced to 6mm from 12 mm.
3. The hypersonic aircraft rectangular cross-section nozzle of claim 1, wherein the circumferential stiffener is a carbon fiber/phenolic composite.
4. The hypersonic aircraft rectangular cross-section nozzle of claim 1, wherein the metallic shield is a superalloy material.
5. The hypersonic aircraft rectangular cross-section nozzle of claim 1, wherein the insulation board is a nanoporous aerogel insulation composite.
6. The hypersonic aircraft nozzle of claim 1 wherein the thermal blanket is an aluminum silicate fiber matrix material.
CN202011439429.2A 2020-12-07 2020-12-07 Rectangular cross-section spray pipe Active CN112727634B (en)

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CN112727634B true CN112727634B (en) 2022-08-16

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Publication number Priority date Publication date Assignee Title
US3398896A (en) * 1965-12-30 1968-08-27 Air Force Usa Supersionic convergent-divergent jet exhaust nozzles
CN102788677A (en) * 2012-09-03 2012-11-21 中国科学院力学研究所 Hypersonic mach-number-variable wind tunnel nozzle
CN205532924U (en) * 2015-11-06 2016-08-31 上海新力动力设备研究所 Yawing force engine jet pipe
CN106438103A (en) * 2016-05-30 2017-02-22 西北工业大学 S-shaped bent shrinking-expanding spray pipe structure
CN108956082A (en) * 2018-09-20 2018-12-07 中国空气动力研究与发展中心超高速空气动力研究所 A kind of rectangular nozzle
CN110588014A (en) * 2019-09-03 2019-12-20 长春长光宇航复合材料有限公司 2.5D composite material spray pipe expansion section and co-curing forming method thereof
CN111159814A (en) * 2019-12-19 2020-05-15 中国航天空气动力技术研究院 Design method and configuration of rectangular supersonic velocity spray pipe with turning inlet and high slenderness ratio

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US3398896A (en) * 1965-12-30 1968-08-27 Air Force Usa Supersionic convergent-divergent jet exhaust nozzles
CN102788677A (en) * 2012-09-03 2012-11-21 中国科学院力学研究所 Hypersonic mach-number-variable wind tunnel nozzle
CN205532924U (en) * 2015-11-06 2016-08-31 上海新力动力设备研究所 Yawing force engine jet pipe
CN106438103A (en) * 2016-05-30 2017-02-22 西北工业大学 S-shaped bent shrinking-expanding spray pipe structure
CN108956082A (en) * 2018-09-20 2018-12-07 中国空气动力研究与发展中心超高速空气动力研究所 A kind of rectangular nozzle
CN110588014A (en) * 2019-09-03 2019-12-20 长春长光宇航复合材料有限公司 2.5D composite material spray pipe expansion section and co-curing forming method thereof
CN111159814A (en) * 2019-12-19 2020-05-15 中国航天空气动力技术研究院 Design method and configuration of rectangular supersonic velocity spray pipe with turning inlet and high slenderness ratio

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薄壁大尺寸铌钨合金喷管精密旋压成形工艺研究;雒亚涛、翟宝力;《火箭推进》;20161231;第42卷(第6期);第68-73页 *
高性能二元收敛喷管型面设计方法;李娜、吉洪湖;《航空发动机》;20191030;第45卷(第5期);第1-6页 *

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