Xin được hỏi các bác là hiện nay các trang mạng của Trung Quốc như sinodefense.com và bbs.tiexue.net nói rằng 8/1996 Nga đã bán toàn bộ tài liệu kỹ thuật , bản vẽ hoàn chỉnh của động cơ P-79-300 và năm 1997 là phiên bản P-79-300B của máy bay Yak-141 để TQ chế tạo được động cơ WS-15 vậy thực hư sự việc này như thế nào mong các bác giải đáp cho em vụ này?
Xin được trích nguyên văn trên
www.sinodefenceforum.comIntroduction to Chinese WS15
Turbofan 15 (WS15) grade turbofan 15 named "Fabri" military turbofan engines use Turbo-fan Jet engine turbofan engine type Chief Designer Jiang Hefu national China Research Institute of China gas turbine manufacturer Xian machine engine company/Li Yang Guizhou aviation engine company object WS-15-10 for J-10M (export) WS-15-13 J-13 single general layout of abdominal DSI intake stealth fighter. WS-15-CJ for a study of vertical/short take off landing fighter. (CJ is Chuizhiqijiang Jianjiji letter of the first vertical take off and landing fighter shorthand) WS-15X for double-billing of heavy lead flight test of the stealth fighter.
In the Russia Yu 1992 spring began expand hard negotiations, in after 3 years of saw zhihou, because Russia of economic status is difference, for military research of funding rarely rarely, and because in 92 Minsk maqiulisha meeting ya grams-141 was terminated Hou, P-79 engine no has using object, and no other of fighter using this engine, so "Union" aviation engine research production Consortium (original Paul mansky engine shejiju) of economic status is difference, in this status Xia, June 1995, in the Russia signed has transfer P-79 engine production license of agreement, August 1996, Russia of "Union" aviation engine research production Consortium (original Paul mansky engine shejiju) to China aspects delivery has P-79 engine of full design drawings and the technology information, especially introduced has manufacturing P-79 engine core machine of production device and the production manufacturing technology information. regrets of is for ya grams-141 of P-79B-300 engine vector nozzle technology is no are, then is as a vertical landing fighter of vortex fan engine for pre-inquiry, but this vertical landing fighter with many China yiqian development of aircraft as. (Later, in 1998 when the Asian financial crisis Russia economy were also multiple crises, China not only purchased for ya-g-141 P-79B-300 engine nozzle technology, but also made the Moscow Union of Aero-Engine technology group developed the thrust of 20 tons of R179-300 engine design and P-79M design drawings and technical data. R179-300 engine is the engine for vertical takeoff fighter Jacques 141 research and further development of the R-79V-300 engine. ) In this background Xia, 1996 early, River and Fu collaborative Liu Da ring academician is responsible for organization "95" Defense major background (vertical landing fighter of plan) of pre-inquiry project--a new Vortex fan engine (to P-79 engine for Foundation for depth development) key technology pre-inquiry work, surveying and mapping imitation P-79 engine of core machine, organization completed has P-79 engine of high pressure pressure gas machine, and combustion chamber, and turbine three large core part, proportion of surveying and mapping imitation of work. for theory method, and calculation method and test method of exploration research; to breakthrough advanced part key technology mainly, focus around three large high pressure part, proportion full size test pieces of design and trial and the test to and related of strength, and control, system for comprehensive application research, in three large core part of surveying and mapping imitation in the, bold advocate used has aviation power many frontier design technology results and large application new material, and new technology, to breakthrough has more than 120 more than item key technology.
624 made the Moscow Union of Aero-Engine technology group developed the thrust of 20 tons of R179-300 engine design and P-79M design drawings and technical information, development YWH 130-27 core machine, YWH 130-27 core engine is based on the P-79 engine core engine as the basis for the further development of. CJ-2000 is based on YWH
30-27 core engine as the basis for further development, development WS-15 is the CJ-2000 version of code. (CJ is vertical landing fighter of Chuizhiqijiang Jianjiji letter first a shorthand, 2000 is project began development of time is 2000) 1999 national day Hou, 624 by reference R179-300 and P-79M of engine design programme, launched has to YWH 130-27 core machine for Foundation of improved design programme, in compete for next generation fighter fighter-13 of engine Shi, get victory,, 2000 early official was selected for fighter-13 singles general layout abdominal DSI inlet of stealth fighter aircraft of power plant. The number is WS-15. Named "Fabri" turbofan. superior requires the "WS-15" engine development to fully implement the new military standard GJB241-87 "General specification for aviation turbine air-jet and turbofan engines and full implementation of the structural integrity of the engine framework. At the same time decided to include the development of WS-15 is divided into three phases: three high pressure development of performance parts and the core development research, develop, validate and prototype of the machine. This WS-15 project development, this is my first time to follow the "key technology breakthroughs-advanced basic research-development-model-validation machine parts-core machine" by this development model of turbofan engine development work, so it can be said to be a milestone significance! Comprehensive development work began in early 2000. (Sliding the machine validation machine was given in 1997, in 1999 due to financial reasons forced to abort. Actually is for WS-15 way and horse, and not because WS10 engine or due to funding causes) from recently held of China gas turbine Institute (624 by) work will Shang was informed that, in China itself development of thrust thrust-weight than for 9 of turbine fan aviation engine of core machine CJ2000 Yu on April 14, 2005 first ignition success Hou, thrust-weight than for 9 of turbine fan aviation engine of core machine has Yu July 2005 early in Taiwan frame running test Shi, various performance full reached has design index, speed push to ground highest speed (conversion speed 102.2%)-----"e eyebrow" aviation engine of technology validation machine in May 2006 first Taiwan frame running test success. This indicates that China's autonomous development of Aero-Engine and on the road to achieve a historic leap forward, in the development of China's fourth generation midsize fighter took a solid fundamental step on the journey. March 2007 prototype machine bench running successfully for the first time, is expected in June 2009, "Fabri" engine prototypes will complete the FRET (flight identification before the pilot phase), the end of June 2009 with J-13 first flight successful. for 60 anniversary of the motherland and offered soup gift. expected to be completed March 2013 engine design type testing. Stereotypes of July 2014 production engine, installed "Fabri" aero-engine of fourth generation single medium fighter (J-13) in 2013, with initial operational capability.
In accordance with the aircraft mission requirements, "Fabri" choosing higher cycle parameters of aeroengine turbine inlet temperature, moderate overall pressure ratio of culvert road and lower than. Used of technology main has injury capacity limited and efficient of wide string leaves, and three dimensional viscous leaves turbine design method, and overall leaves disk structure of fan and pressure gas machine, and single crystal gas cold turbine leaves, and powder metallurgical turbine disk, and brush type seal strict, and resin base composite outside culvert machine casing, and overall type Afterburner combustion chamber design, and ceramic base composite nozzle regulation tablets, and ternary vector nozzle and has fault diagnosis and State monitoring ability of double more than of type full digital type electronic control system. Engine is composed of 10 units.
"Fabri" structure and system of turbofan engine inlet ring, air inlet casing for all titanium structure. With 18 variable camber inlet guide vanes, the front for radial support plate, rear adjustable parts, edge is to air from the high pressure compressor ice. Fan 3-stage axial-flow. Wide-chord fan blades of solid titanium alloy. 1th stage fan blades with the wide chord design, removable fan blades, with a middle boss. 2nd and 3rd stage fan to simple linear friction welding technology of welding into a blisk structure. Fan casing is a ring structure, the fan rotor made of removable, the 2nd-level disc front and rear with drum loops, and respectively, 1th disk connectivity. Boost almost 4.01. 3-level design of stator and rotor are three-dimensional flow. 6 stage axial-flow in high pressure compressor. Boost than 7.16. Level 3 before rotor disc structure as a whole, are forging on with electrochemical machining. 3 after stage rotor blades through Chevron rabbet and disc connection. Titanium alloy for the first 3 stationary blade material. Rotor for hybrid structure of electron beam welded and bolted, using three-dimensional flow design. Stator part of inlet guide vanes and the 1th, 2 stationary blade adjustable level 3 disk made of high-temperature titanium alloy before, both before and after the 2nd-level disk with drum loops, and respectively, 1th disk connectivity. Di4~6ji plate made from nickel-Base Superalloy powder metallurgy, electron beam welding is a body, with long bolt front and 3rd-level disk connected together. Opposite to the mediation case as a whole and for titanium alloy compressor casing, a borescope peep hole, for the observation of rotors and other parts.
Combustion chamber short concentric type. The flame tube uses the laser drilling the vesicular structure to carry on cooling. The flame tube double-decked floats the wall type structure for the whole, the outer layer for the whole ring-like shell, uses the binary channel spray nozzle, the fuel oil spouts after 22 bipyramid spray nozzles and 22 eddy cups and atomizes, realizes the smokeless combustion, has the even export temperature field. High pressure turbine single stage axialflow type. Uses the domestic second generation of unit crystal turbine blade material, the heat insulation coating and the advanced cooling structure. The single stage axialflow type, does not bring the crown. Uses gas blanket cooling to add the impingement cooling way. The rotor blade and the stator blade material is the domestic second generation of unit crystal material, on the leaf blade has the physical gas phase deposition heat insulation coating. The engine case inside lining fan-shaped section carries on the tip clearance control through the cooling air. The rotor blade and the guide apparatus may replace alone. The turbine wheel part uses the haploid structural design, after turbine rotor, guide apparatus, turbine casing, turbine wheel the engine case and the bearing engine case and so on five modules compose. Low pressure turbine single stage axialflow type. With high-pressure spool to extension. The hollow air-cooled rotor leaf blade, brings the crown. The rotor blade may replace alone, the stator blade may partition the replacement. Still had used the low pressure turbine guide apparatus. The low pressure turbine wheel disk center opens has the pocket, with the aim of installing high-pressure spool's rear bearing (intermediary bearing). Afterburner integral type. Uses the radial direction flame stabilizer. The flame stabilizer is composed of 1 “V” the shape center flame stabilizer with 36 radial direction stablers. The radial direction stabler uses the ventilator air cooling. The thrust augmentation tube body uses is flame-resistant the titanium alloy to reduce the weight, tube in vivo does has the heat insulation sleeve, outside both's slit average crosses contains the air to carry on cooling to the tube body, the center ring-like flame stabilizer makes 12 sections along the circumference, may the free expansion, whole set flame stabilizer be possible, in the engine installs under airplane's condition carries on the replacement, the tail pipe entire journey adjustable restraining - expansion type, uses three Yuan vector nozzles, may make ±25° the deflection in the pitching direction. From +25° to - 25° the traveling schedule in only needs 1.5 seconds. Uses in adjusting the airplane pitching flight attitude. Is loaded with the advanced ceramic base compound materials tail pipe to adjust the proglottis. The control system thrust force and the vector by the double redundancy entire jurisdiction digit electronic control system control (FADEC), according to the ventilator rotational speed and the core machine-pressed ratio adjustment engine work, have the failure isolation function. [engineering data]Biggest thrust augmentation thrust force (daN) 16186.5 middle thrust force (daN) 10522 thrust augmentation oil consumption (kg/daN/h) 2.02 middle oil consumption (kg/daN/h) 0.665 thrust ratio 8.86 air flow (kg/s) 138 vectored thrust compared to 0.382 total supercharger ratio 28.71 turbine wheel intake temperature (℃) 1477 most large diameter (mm) 1.02 length (mm) 5.05 quality (kg) 1862.3
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