GP7000 was developed from GE90 of GE Company and PW4090 of Pratt & Whitney Company. ETOPS is a derivative product based on mature technology and constantly improved, which coincides with the idea that rolls royce Company designed Trent 900 for A380. Trent 900 and GP7000 are brand-new engines, but their technologies are based on proven and mature technologies, and they are constantly improved and innovated on this basis, and then follow suit-successfully developed engines with a considerable thrust level.
Component characteristics
The mechanical part of GP7000 consists of GE's core machine, Pratt & Whitney's low-voltage part and gearbox. GE's core machines include: 9-stage high-pressure compressor, 2-stage high-pressure turbine and low-emission single-ring combustion chamber; Pratt & Whitney's low-pressure parts include: 1 stage fan, 5-stage low-pressure compressor and 6-stage low-pressure turbine.
The fan adopts hollow titanium alloy wide chord swept back fan blades. In order to reduce fan vibration, improve the ability to resist foreign object damage and reduce blade quality, Pratt & Whitney has been used in PW4084. The blades of the hollow fan are not absolutely hollow, and some reinforcing structures are adopted in the cavity. The function of swept back is to reduce the normal component of relative Mach number at the blade tip entrance, thus reducing the shock wave loss of blades and improving the efficiency of fans. Trent 900 also uses titanium alloy swept-back fan blades with wide chords, which shows that swept-back design has gradually become the mainstream of fan blades. The containment system is made of Kevlar aluminum composite material, which is light in weight and corrosion resistant. GP7000 high-pressure compressor has absorbed the design experience of GE from CF6, CFM56 to GE90. The pressure ratio of the 9-stage high-pressure compressor is 19, which is 0.72 less than that of the GE90 engine, and the number of compressors is reduced by 1. Its characteristics are: the low aspect ratio blade with three-dimensional aerodynamic design has higher efficiency, can prevent foreign body damage and better stall margin; The thermal matching casing and rotor are adopted to reduce the friction between blades, thus ensuring high aerodynamic performance; 1 stage wide chord forward swept blisk simplifies the assembly structure and reduces the maintenance cost.
The combustion chamber has a single-ring structure, simple structure and low exhaust emission. The inner and outer walls of the flame tube are cooled by porous gas film, and the head is equipped with a high-pressure air atomizing nozzle. Single crystal alloy baffle can improve the durability of the head and has good high temperature oxidation resistance. The scheme of rich oil-rapid mixing-lean oil combustion is adopted, which optimizes the gas residence time in the combustion chamber, reduces the emission, meets the current and future emission standards of CAEP4, and has a certain margin. On the other hand, it can also meet the requirements of air re-ignition.
The HP turbine inherits the two-stage axial flow of GE90. The turbine rotor blade is made of Rene N5 single crystal nickel-based alloy, and the wheel disc is made of a new nickel-based powder alloy with damage tolerance, numbered ME3. These materials are studied for supersonic civil transport aircraft engines, and their high-temperature strength, high-temperature low-cycle fatigue life and high-temperature crack propagation have been improved and improved. The flange of high-pressure turbine disk has no holes to improve the strength, and at the same time, it can reduce the wind resistance loss caused by bolt heads and nuts and reduce the maintenance cost.
The design goal of GP7000 low-pressure turbine is to improve the efficiency and reduce the cost by combining the design of high-lift three-dimensional blades with the reasonable circumferential relative position of guide vanes at all levels of low-pressure turbine. The floating center ring is used to seal the low-pressure rotor, so as to control the radial clearance well. The optimization of axial clearance between turbine rotor blades and stator blades is helpful to reduce engine noise.
Different from Rolls-Royce's three-rotor structure, GP7000 follows the mature twin-rotor engine structure of GE and Pratt & Whitney, with the advantages of simple structure and fewer bearings, fuel tanks, seals and frames. The unit structure simplifies engine maintenance. The compact, high-rigidity high-pressure rotor and "brittle" bearing used by Pratt & Whitney on PW4090 can improve the performance retention ability and prolong the engine on the wing.
control system
The control system of GP7000 is the third generation full authority digital electronic control system (FADEC III) provided by GE. Although the FADEC III was developed on the basis of the successful operation experience of the first two generations of GE Company, compared with the previous FADEC device, the third generation product has a speed of 10 times and a storage capacity of 8 times, which provides greater control system redundancy, thus improving the reliability of engine control and having the ability to upgrade technology in the future. It will become the standard configuration of all GE large civil engines in the future. FADECⅲ Ⅲ will be in service on GE90- 1 15B and CFM56-7 for several years before it is used on GP7000. FADEC III dual-channel processor can completely operate all engine control systems, allowing single-parameter faults and various multi-parameter faults without adversely affecting engine work. When the engine detects that one of the two channels is out of order, FADEC III actively switches the main engine control system to the standby channel, and informs the fault monitoring system of the engine and the aircraft of the fault. This function benefits from the new analog diagnosis technology adopted by GP7000.
FADEC III's high-speed processor and mass storage will allow fault diagnosis logic to be added to a highly simulated engine performance model for the first time. By calculating the value of "virtual sensor" and comparing it with other measured engine parameters, it can be identified whether a sensor fails or other components fail.
The electronic quantitative debris monitor (QDM) of GP7000 can eliminate the need to manually check the magnetic debris detector in the lubricating oil system on a regular basis. The equipment has been used in GE90 engine, and its operation has proved its reliability. It can accurately predict the abnormal damage of bearings or other oil-bearing parts.
GP7000 is the first engine with advanced signal filtering function in FADEC, which can isolate and diagnose the vibration with impending hardware damage symptoms. The pre-determination of vibration signal is convenient to decide whether to maintain the aircraft immediately or allow it to continue operating.
All these will improve the on-time arrival rate of aircraft and prevent destructive engines from stopping in the air.
Performance summary
GP7000 has two engines with different thrust levels, namely GP7270, thrust 3 1 1KN, bypass ratio 8.7, total pressure ratio 43.9, length 4.75m, diameter 3. 16m, which is used for 560t A380-800. GP7277 has a thrust of 340 kN, a bypass ratio of 8.7, and a total pressure ratio of 45.6. Its length and diameter are the same as those of GP7270, and it is used for a 590-ton A380-800 cargo plane. The thrust of these two engines remains constant at an altitude of 30℃. Moreover, with the increasing thrust requirement of A380 aircraft, GP7000 can make the thrust exceed 374 kN within the same frame size by slightly modifying the fan and high-pressure turbine.
In order to reduce noise, GP7000 adopts a large bypass ratio (about 9), which reduces the fan pressure ratio. A large axial spacing is adopted between the rotor blades of the fan and the outlet guide blades of the special-shaped fan; Optimize the number of rotor blades and stator blades on low-pressure compressors and low-pressure turbines to reduce noise sources; A serrated core exhaust nozzle is also designed. The goal of "Engine Alliance" is that the A380 aircraft equipped with GP7000 can meet the noise level requirements of QC 1 and QC2 of London Heathrow Airport at the maximum takeoff weight.
The three-dimensional aerodynamic design of the whole aircraft makes the efficiency of the impeller parts of GP7000 reach a very high level, improves the fuel efficiency of the engine, reduces the operating cost, and helps to realize the design voyage of A380 with the maximum14820km. Trent 900 engine of rolls royce Company is the starting engine of Airbus A380, and it is also the first design.
The engine is scheduled to be put into operation in March 2003. This type of engine was certified as planned in June 5438+ 10, 2004.
The first A380 aircraft with Trent 900 engine made its first flight in April 2005. put in force
The thrust of type A engine ranges from 70,000 pounds to 76,500 pounds, but its certified thrust is as high as 80,000 pounds. Trent 900 engine has been flying on A380 for more than 7500 hours, and has been running and flying on the ground.
Nearly 30,000 cycles were completed on the plane. Of the five A380 participating in the development plan, four are manufactured by Rolle.
Rolls-Royce engines provide power. During the test plan, the Trent 900 engine proved to be an extremely
Reliable engine once again proves the advantages of Rolls-Royce's low-risk method in engine design. In the flight test, this type of engine completed the test under extreme test conditions such as severe cold, extreme heat and high performance, which made
The A380 aircraft has reached a height and speed that has never been achieved in operation, and the minimum requirements needed to keep the aircraft flying.
Speed. The test results are excellent, and the performance prediction is verified, so that Trent 900 engine can meet all requirements as planned.
Key target. Trent 900 engine is the lightest and most environmentally friendly engine used in A380 aircraft. This engine is the cleanest in the world.
The large thrust engine is also the quietest engine used in A380 aircraft. In addition, the engine is Rolls Royce.
The largest engine diameter manufactured by the company so far is close to 10 foot. The engine has passed the aircraft noise certification, which shows that it can easily meet the requirements of airports including London Heathrow Airport.
Use strict QC 1 and QC2 restrictions. Heathrow Airport is the first customer of A380 aircraft, and Singapore Airlines plans to do the same.
One of the original destinations of A380 aircraft. Singapore Airlines plans to receive the first A380 aircraft in 2007. Among 1 1 airline customers who chose A380 engine, seven chose Trent 900 engine.
The market share of this engine in confirmed and intended aircraft will reach 565,438+0%. These seven airlines are Singapore.
Airlines, Virgin Atlantic, Qantas, Lufthansa, Malaysia.
West Asia Airlines, Etihad Airways, China Southern Airlines. Trent 900 engine has been manufactured since 1995, when Trent 700 engine first flew on A330.
The fourth member of the seven members of Delta series engines. Rolls-Royce developed Trent 900 engine with global partners. 7 Company as a risk
The R&D plan of the engine is participated by the partners with revenue of * * *(revenue * * *), namely ITP and Hamilton in Spain.
Sundstrand, Goodrich and Honeywell in America, Avio in Italy.
Volvo Airlines of Sweden and Marubeni Corporation of Japan. In addition, South Korea's Samsung Technology (Samsung
Techwin), Kawasaki Heavy Industries of Japan and Ishikawa Island Broadcasting and Grinding Heavy Industries also participated in the project. "Amazing Data" of Trent 900 Engine When taking off, the thrust provided by the four Trent engines of A380 is equivalent to that of more than 3,500 family cars! The engine fan sucks in more than 1.25 tons of air per second, and when the air leaves the nozzle at the rear of the engine, the air accelerates to.
Nearly 1 0,000 mph (10,600 km/h). Trent engine overhaul interval is about 13000 flight hours, which is equivalent to flying 7 million miles ... or traveling around the world.
250 laps. The combustion temperature of fuel in the combustion chamber of Trent engine is as high as 2000 degrees Celsius. Because when the temperature exceeds 1300 degrees Celsius, the hair
The metal in some parts of the engine will begin to melt, so the engine adopts a precise cooling system.