CN114810662A - Compressor rotor blade ring and compressor - Google Patents
Compressor rotor blade ring and compressor Download PDFInfo
- Publication number
- CN114810662A CN114810662A CN202210402045.6A CN202210402045A CN114810662A CN 114810662 A CN114810662 A CN 114810662A CN 202210402045 A CN202210402045 A CN 202210402045A CN 114810662 A CN114810662 A CN 114810662A
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- China
- Prior art keywords
- ring body
- blade
- tenon
- ring
- compressor rotor
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- Pending
Links
- 230000007704 transition Effects 0.000 claims abstract description 11
- 238000007789 sealing Methods 0.000 claims description 43
- 229910000838 Al alloy Inorganic materials 0.000 claims description 12
- UQZIWOQVLUASCR-UHFFFAOYSA-N alumane;titanium Chemical compound [AlH3].[Ti] UQZIWOQVLUASCR-UHFFFAOYSA-N 0.000 claims description 12
- 239000000463 material Substances 0.000 claims description 11
- 239000011159 matrix material Substances 0.000 claims description 11
- 239000002131 composite material Substances 0.000 claims description 10
- 239000000835 fiber Substances 0.000 claims description 7
- 229910010038 TiAl Inorganic materials 0.000 claims description 4
- 238000003466 welding Methods 0.000 abstract description 13
- 230000001133 acceleration Effects 0.000 abstract description 5
- 230000009286 beneficial effect Effects 0.000 abstract 1
- 229910045601 alloy Inorganic materials 0.000 description 8
- 239000000956 alloy Substances 0.000 description 8
- 238000000034 method Methods 0.000 description 5
- 239000010936 titanium Substances 0.000 description 5
- 238000005457 optimization Methods 0.000 description 2
- 229910001069 Ti alloy Inorganic materials 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 230000005489 elastic deformation Effects 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 238000001513 hot isostatic pressing Methods 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 229910000601 superalloy Inorganic materials 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
- F04D29/322—Blade mountings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/02—Selection of particular materials
- F04D29/023—Selection of particular materials especially adapted for elastic fluid pumps
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention relates to a compressor rotor blade ring and a compressor, belonging to the technical field of engines and comprising a ring body and a plurality of blades which are uniformly distributed along the circumferential direction of the ring body, wherein each blade is provided with a blade body, a tenon and a flange plate arranged between the blade body and the tenon; the tenon is provided with a transition section close to the ring body, and two opposite sides of the transition section are provided with inwards concave curved surfaces, so that the curved surfaces between the adjacent tenons form a gap; the bottom of tenon has curved terminal surface, and the surface coordination of terminal surface and ring body, and the terminal surface welding of tenon is in the surface of ring body. The invention has the beneficial effects that: the connection strength of the blades and the ring body is improved, the weight of the rotor is reduced, the temperature resistance of the blades is improved, and the acceleration performance of the engine is improved.
Description
Technical Field
The invention relates to the technical field of engines, in particular to a compressor rotor blade ring and a compressor.
Background
The pneumatic load of future aeroengine is high, total pressure ratio is high, flight mach number is high, compressor back stage rotor operating temperature improves by a wide margin, and traditional superalloy can't satisfy the temperature resistant requirement, and the attempt of using novel high temperature resistant alloy to make the blisk at home and abroad in recent years, however, because of material density is big, simultaneously, the structure of current blade and ring leads to needing blade and the ring body of bigger volume for rotor weight improves by a wide margin, is unfavorable for the acceleration performance of engine.
In order to solve the problems, the invention provides a compressor rotor blade ring and a compressor.
Disclosure of Invention
In order to solve at least one of the technical problems, the invention provides a compressor rotor blade ring, which comprises a ring body and a plurality of blades uniformly distributed along the circumferential direction of the ring body, wherein each blade is provided with a blade body, a tenon and a flange plate arranged between the blade body and the tenon, and the flange plate extends towards two sides at the root of the blade body along the axial direction of the blade ring; the tenon is provided with a transition section close to the ring body, and two opposite sides of the transition section are provided with inwards concave curved surfaces, so that the curved surfaces between the adjacent tenons form a gap; the bottom of tenon has curved terminal surface, the terminal surface with the surface coordination of ring body, just the terminal surface of tenon weld in the surface of ring body.
Adopt above-mentioned structure, the blade welds through tenon and ring body, can increase the connection cross-section of blade and ring body by a wide margin, thereby improve the joint strength of blade and ring body, and simultaneously, the changeover portion of indent has on the tenon, adjacent indent curved surface forms the space, under the prerequisite that satisfies joint strength, reduce the volume as far as possible, thereby reduce the weight of rotor, improve the acceleration performance of engine, the welding process hole also can be regarded as to the space simultaneously, be favorable to the welding, reduce the welding degree of difficulty, design through interface structure, tenon arc end face structure and space structure, can realize welding process's feasibility.
Preferably, the blade is made of titanium-aluminum alloy; the ring body is made of a continuous fiber reinforced titanium-aluminum alloy matrix composite material.
Preferably, the titanium alloy is a TiAl alloy; the titanium-aluminum alloy matrix is Ti 2 An AlNb alloy.
Preferably, a bonding layer is arranged between the tenon and the ring body, and the bonding layer comprises the material of the tenon and the material of the ring body base body.
Preferably, a left sealing structure and a right sealing structure for sealing the gap are arranged between the blade and the ring body, and the left sealing structure and the right sealing structure are respectively arranged on two sides of the gap; each sealing structure comprises a plurality of sealing sheets, and the sealing sheets are drum-shaped elastic sheets.
Preferably, the flange plate has two functional structures, each functional structure is provided with a first clamping groove protruding towards the ring body, a second clamping groove protruding towards the flange plate section is arranged on the outer surface of the ring body, and an opening of the first clamping groove and an opening of the second clamping groove are oppositely arranged and are used for fixing two ends of the sealing piece.
Preferably, both ends of the sealing piece are respectively provided with a raised stop hook; at least one inner side wall of the first clamping groove and at least one inner side wall of the second clamping groove are provided with grooves matched with the stop hooks, and the grooves are used for circumferential limitation of the sealing sheets.
Preferably, the ring body further comprises a drum and a mounting edge for connecting adjacent rotor blade rings, and the drum and the mounting edge extend to two sides respectively along the axial direction of the rotor blade rings.
A compressor comprises the compressor rotor blade ring.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate exemplary embodiments of the invention and together with the description serve to explain the principles of the invention.
FIG. 1 is a schematic structural diagram of an embodiment;
FIG. 2 is a cross-sectional view of a rotor blade ring;
FIG. 3 is a schematic view of a blade configuration;
FIG. 4 is a left side view of FIG. 3;
FIG. 5 is a schematic structural view of the ring body;
FIG. 6 is a schematic view of the structure of the sealing sheet;
fig. 7 is a left side view of fig. 6.
In the figure: 1-blade, 2-ring body, 3-sealing piece, 4-binding layer, 5-blade body, 6-flange plate, 7-tenon, 8-first clamping groove, 9-end surface, 10-curved surface, 11-groove, 12-base body wrapping part, 13-composite material part, 14-drum barrel, 15-second clamping groove, 16-stop hook, 17-mounting edge, 18-drum part and 19-gap.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and embodiments. It is to be understood that the specific embodiments described herein are for purposes of illustration only and are not to be construed as limitations of the invention. It should be noted that, for convenience of description, only the portions related to the present invention are shown in the drawings.
In addition, the embodiments of the present invention and the features of the embodiments may be combined with each other without conflict. The present invention will be described in detail below with reference to the accompanying drawings in conjunction with embodiments.
As shown in fig. 1-7, a compressor rotor blade ring comprises a ring body 2 and a plurality of blades 1 uniformly distributed along the circumferential direction of the ring body 2, as shown in fig. 3 and 4, each blade 1 has a blade body 5, a tenon 7 and a flange 6 arranged between the blade body 5 and the tenon 7, and the flange 6 extends towards two sides at the root of the blade body 5 along the axial direction of the blade ring; the tenons 7 are provided with transition sections close to the ring body 2, and two opposite sides of the transition sections are provided with inwards concave curved surfaces 10, so that the curved surfaces 10 between the adjacent tenons 7 form a gap 19; the bottom of tenon 7 has curved terminal surface 9, and terminal surface 9 and ring body 2's surface coordination, and the terminal surface 9 of tenon 7 welds in ring body 2's surface.
In traditional structure, blade 1 adopts the joint etc. to dismantle with ring body 2 and is connected, but the joint strength of this structure is low, poor stability, and the required component of detachable construction is more, the volume is bigger, can improve the weight of rotor by a wide margin, be not suitable for the aeroengine that the load is high, prior art also has the adoption welded connection, concrete scheme is that blade 5 is direct and ring body 2 welds, nevertheless because blade 5 is the slice, bulk strength is very low, and the clearance between the adjacent blade 1 is less, the welding is difficult to realize.
According to the technical scheme, the blade 1 is welded with the ring body 2 through the tenon 7, the tenon 7 is not a long and narrow sheet but is in a square structure, the connecting section of the blade 1 and the ring body 2 can be greatly increased, so that the connecting strength of the blade 1 and the ring body 2 is improved, meanwhile, the tenon 7 is provided with an inwards concave transition section, and a gap 19 is formed by adjacent inwards concave curved surfaces 10, so that on the premise of meeting the connecting strength, the size is reduced as much as possible, the weight of a rotor is reduced, the acceleration performance of an engine is improved, meanwhile, the gap 19 can also be used as a welding process hole, welding is facilitated, the welding difficulty is reduced, and the feasibility of a welding process can be realized through the design of an interface structure and the structures of the arc end surface 9 and the gap 19 of the tenon 7.
In the structure, the blade body 5, the tenon 7 and the flange plate 6 are integrally formed, the strength of the blade 1 is ensured, the blade body 5 and the surface of an airflow channel are processed after being welded into an integral blade ring, and the part below the flange plate 6 and the tenon 7 can be welded after being processed;
regarding the structure of the tenon 7, the tenon 7 disclosed by the invention is different from the traditional tenon 7/mortise structure, does not need a matching surface, is only welded with the outer cylindrical surface of the ring body 2 on the bottom cambered surface, the outer surface of the transition section is designed after topological optimization on the basis of meeting the bearing capacity,
specifically, the transition section is located in the middle of the tenon 7, so that the connection area of the two ends of the tenon 7 is ensured to be the largest, and the connection strength of the blade body 5 and the tenon 7 and the connection strength of the blade 1 and the ring body 2 are improved; moreover, the concave curved surface 10 can be arranged in the middle of the tenon 7 and is designed after topological optimization on the basis of meeting the bearing capacity, that is, on the premise of meeting the strength of the tenon 7, the weight of the rotor is reduced as much as possible, and the acceleration performance of the engine is improved.
In one embodiment, the blade 1 is made of titanium-aluminum alloy; the ring body 2 is made of a continuous fiber reinforced titanium-aluminum alloy matrix composite material. Specifically, the blade titanium-aluminum alloy is preferably a TiAl alloy; the annular titanium-aluminum alloy matrix is preferably Ti 2 An AlNb alloy.
By adopting the materials, the high-temperature resistance of the blade 1 can be obviously improved, the requirement of the blade on the temperature resistance of 800 ℃ is met, and the high-temperature resistance of the blade is improvedThe temperature capability is high, the TiAl density is low, the centrifugal load of the rotor is greatly reduced, and the continuous fibers are adopted to reinforce Ti 2 The ring body 2 is designed by the AlNb alloy matrix composite material, so that the bearing capacity of part of the ring body 2 is improved, and the structural weight is further reduced.
Overall, the blade ring structure adopted by the invention has high temperature resistance, strong bearing capacity, light weight, good economical efficiency and good process realizability.
As for the material of the ring body 2, continuous fiber reinforced Ti is adopted 2 The AlNb is prepared, the ring body 2 comprises a composite material part 13 and a matrix sheath part 12, the composite material part 13 is reinforced by SiC fibers, the composite material is wound in a ring groove prefabricated by a sheath and is made into a ring blank through hot isostatic pressing, and the matrix sheath is Ti 2 And the AlNb alloy wraps and protects the composite material, the matrix sheath is used for welding with the external blade 1, and the blade 1 is machined into a blade ring after being welded.
As shown in fig. 5, regarding the structure of the blade ring, the ring body 2 further includes a drum 14 and a mounting edge 17 for connecting adjacent rotor blade rings, the drum 14 and the mounting edge 17 respectively extend to two sides along the axial direction of the rotor blade ring, the mounting edge 17 is used for connecting with other rotor stages, and the second locking groove 15 is opened at the end of the drum 14.
In one embodiment, the tenon 7 and the ring body 2 are provided with the bonding layer 4, the bonding layer 4 comprises the material of the tenon 7 and the base material of the ring body 2, the connection strength of the tenon 7 and the ring body 2 is ensured, and the tenon 7 and the ring body 2 are welded through diffusion welding or linear friction welding to realize double-alloy integration.
In one embodiment, a left sealing structure and a right sealing structure for sealing the gap 19 are arranged between the blade 1 and the ring body 2, the left sealing structure and the right sealing structure are respectively arranged at two sides of the gap 19, namely at least two sealing structures are arranged; each sealing structure comprises a plurality of sealing sheets 3, and the sealing sheets 3 are drum-shaped elastic sheets. The sealing sheets 3 play a role in sealing, air is prevented from entering the gap 19, the adjacent sealing sheets 3 are mutually abutted, and the sealing sheets 3 are elastic sheets, so that the weight is reduced as much as possible on the premise of meeting sealing, the weight of a rotor is reduced, and the performance of an engine is improved. In addition, the sealing sheet 3 is in a drum shape protruding outwards, the drum-shaped part is a drum-shaped part 18, and the drum-shaped part 18 has the functions of guiding air flow and reducing air pressure resistance, so that the engine performance is improved.
Specifically in the structure, the flange 6 has two functional structures, and every functional structure is equipped with to the bellied first draw-in groove 8 of ring body 2, is equipped with on the surface of ring body 2 to the bellied second draw-in groove 15 of flange section, and the uncovered relative setting of the uncovered of first draw-in groove 8 and second draw-in groove 15 and be used for the fixed at 3 both ends of the piece of obturating, and the piece of obturating 3 assembles in first draw-in groove 8 and second draw-in groove 15 through elastic deformation. First draw-in groove 8 and second draw-in groove 15 all are arc recess 11, and the interior circle of reason board section is located to first draw-in groove 8, and the excircle of ring body 2 is located to second draw-in groove 15.
In order to limit the sealing sheet 3 and prevent the sealing sheet from moving along the circumferential direction, as shown in fig. 6 and 7, two ends of the sealing sheet 3 are respectively provided with a raised stopping hook 16; at least one inner side wall of the first clamping groove 8 and at least one inner side wall of the second clamping groove 15 are provided with grooves 11 matched with the stop hooks 16, the stop hooks 16 are clamped in the grooves 11, and the grooves 11 are used for circumferential limitation of the sealing sheets 3. Of course, the locking hooks 16 can be arranged in a plurality of positions, also can be arranged in the middle and other positions, and only need to be circumferentially limited in a clamping manner.
The invention also discloses a gas compressor, which comprises the gas compressor rotor blade ring. The compressor is used for engines, in particular aircraft engines.
In the description herein, reference to the description of the terms "one embodiment/mode," "some embodiments/modes," "example," "specific example," or "some examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment/mode or example is included in at least one embodiment/mode or example of the application. In this specification, the schematic representations of the terms used above are not necessarily intended to be the same embodiment/mode or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments/modes or examples. Furthermore, the various embodiments/aspects or examples and features of the various embodiments/aspects or examples described in this specification can be combined and combined by one skilled in the art without conflicting therewith.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present application, "plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.
It will be understood by those skilled in the art that the foregoing embodiments are merely for clarity of description and are not intended to limit the scope of the invention. Other variations or modifications will occur to those skilled in the art based on the foregoing disclosure and are within the scope of the invention.
Claims (9)
1. A compressor rotor bling, characterized in that: the blade ring comprises a ring body (2) and a plurality of blades (1) which are uniformly distributed along the circumferential direction of the ring body (2), wherein each blade (1) is provided with a blade body (5), a tenon (7) and a flange plate (6) arranged between the blade body (5) and the tenon (7), and the flange plate (6) extends towards two sides at the root of the blade body (5) along the axial direction of the blade ring;
the tenon (7) is provided with a transition section close to the ring body (2), and two opposite sides of the transition section are provided with inwards concave curved surfaces (10), so that the curved surfaces (10) between the adjacent tenons (7) form a gap (19);
the bottom of tenon (7) has curved terminal surface (9), terminal surface (9) with the surface coordination of ring body (2), just terminal surface (9) of tenon (7) weld in the surface of ring body (2).
2. The compressor rotor bling, according to claim 1, characterized in that: the blade (1) is made of titanium-aluminum alloy;
the ring body (2) is made of a continuous fiber reinforced titanium-aluminum alloy matrix composite material.
3. The compressor rotor bling, according to claim 2, characterized in that: the blade titanium-aluminum alloy is TiAl;
the ring body is made of a continuous fiber reinforced titanium-aluminum alloy matrix composite material, and the titanium-aluminum alloy matrix is Ti 2 AlNb。
4. The compressor rotor bling, according to claim 1, characterized in that: a bonding layer (4) is arranged between the tenon (7) and the ring body (2), and the bonding layer (4) comprises the material of the tenon (7) and the base material of the ring body (2).
5. The compressor rotor bling, according to claim 1, characterized in that: a left sealing structure and a right sealing structure which are used for sealing the gap (19) are arranged between the blade (1) and the ring body (2), and the left sealing structure and the right sealing structure are respectively arranged at two sides of the gap (19); each sealing structure comprises a plurality of sealing sheets (3), and the sealing sheets (3) are drum-shaped elastic sheets.
6. The compressor rotor bling, according to claim 5, wherein: the flange plate (6) is provided with two functional structures, each functional structure is provided with a first clamping groove (8) protruding from the ring body (2), a second clamping groove (15) protruding from the flange plate section is arranged on the outer surface of the ring body (2), the opening of the first clamping groove (8) is opposite to the opening of the second clamping groove (15), and the opening is used for fixing the two ends of the sealing piece (3).
7. The compressor rotor bling, according to claim 6, characterized in that: two ends of the sealing sheet (3) are respectively provided with a raised stopping hook (16);
at least one inner side wall of the first clamping groove (8) and at least one inner side wall of the second clamping groove (15) are provided with grooves (11) matched with the stop hooks (16), and the grooves (11) are used for circumferential limiting of the sealing sheets (3).
8. The compressor rotor bling, according to claim 1, characterized in that: the ring body (2) further comprises a drum barrel (14) and a mounting edge (17) which are used for connecting adjacent rotor blade rings, and the drum barrel (14) and the mounting edge (17) extend towards two sides respectively along the axial direction of the rotor blade rings.
9. A compressor, characterized by: comprising a compressor rotor blade ring according to any one of claims 1 to 8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210402045.6A CN114810662A (en) | 2022-04-18 | 2022-04-18 | Compressor rotor blade ring and compressor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210402045.6A CN114810662A (en) | 2022-04-18 | 2022-04-18 | Compressor rotor blade ring and compressor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114810662A true CN114810662A (en) | 2022-07-29 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210402045.6A Pending CN114810662A (en) | 2022-04-18 | 2022-04-18 | Compressor rotor blade ring and compressor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114810662A (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3304055A (en) * | 1965-03-03 | 1967-02-14 | Rolls Royce | Rotor |
| US3982854A (en) * | 1971-12-20 | 1976-09-28 | General Electric Company | Friction welded metallic turbomachinery blade element |
| DE102008049171A1 (en) * | 2008-09-26 | 2010-04-08 | Mtu Aero Engines Gmbh | Method for producing an integrally bladed rotor and rotor |
| US20160130960A1 (en) * | 2014-11-06 | 2016-05-12 | Techspace Aero S.A. | Mixed Stator for an Axial Turbine Engine Compressor |
| CN109514070A (en) * | 2018-11-30 | 2019-03-26 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of electron beam welded structure leaf dish machining accuracy control method |
| CN210013859U (en) * | 2019-06-14 | 2020-02-04 | 中国航发商用航空发动机有限责任公司 | Axial joggle sealing device of gas compressor and rotor |
| CN213953986U (en) * | 2020-12-17 | 2021-08-13 | 中国航发上海商用航空发动机制造有限责任公司 | Axial-flow compressor and aircraft engine |
-
2022
- 2022-04-18 CN CN202210402045.6A patent/CN114810662A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3304055A (en) * | 1965-03-03 | 1967-02-14 | Rolls Royce | Rotor |
| US3982854A (en) * | 1971-12-20 | 1976-09-28 | General Electric Company | Friction welded metallic turbomachinery blade element |
| DE102008049171A1 (en) * | 2008-09-26 | 2010-04-08 | Mtu Aero Engines Gmbh | Method for producing an integrally bladed rotor and rotor |
| US20160130960A1 (en) * | 2014-11-06 | 2016-05-12 | Techspace Aero S.A. | Mixed Stator for an Axial Turbine Engine Compressor |
| CN109514070A (en) * | 2018-11-30 | 2019-03-26 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of electron beam welded structure leaf dish machining accuracy control method |
| CN210013859U (en) * | 2019-06-14 | 2020-02-04 | 中国航发商用航空发动机有限责任公司 | Axial joggle sealing device of gas compressor and rotor |
| CN213953986U (en) * | 2020-12-17 | 2021-08-13 | 中国航发上海商用航空发动机制造有限责任公司 | Axial-flow compressor and aircraft engine |
Non-Patent Citations (2)
| Title |
|---|
| 侯国清等: "21世纪科学技术展望", 31 July 1994, 科学技术文献出版社, pages: 167 - 168 * |
| 徐德康等: "各国民用飞机发展道路的借鉴和启示", 31 July 2007, 航空工业出版社, pages: 490 - 491 * |
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