CN114486276A - Turboprop aircraft outer lubricating oil system and engine ground rack joint test device - Google Patents
Turboprop aircraft outer lubricating oil system and engine ground rack joint test device Download PDFInfo
- Publication number
- CN114486276A CN114486276A CN202111641463.2A CN202111641463A CN114486276A CN 114486276 A CN114486276 A CN 114486276A CN 202111641463 A CN202111641463 A CN 202111641463A CN 114486276 A CN114486276 A CN 114486276A
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- engine
- lubricating oil
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- nacelle
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- 239000010687 lubricating oil Substances 0.000 title claims abstract description 77
- 238000012360 testing method Methods 0.000 title claims abstract description 43
- 239000003921 oil Substances 0.000 claims description 30
- 230000007246 mechanism Effects 0.000 claims description 7
- 238000006073 displacement reaction Methods 0.000 claims description 5
- 238000005461 lubrication Methods 0.000 claims description 5
- 238000004088 simulation Methods 0.000 abstract description 3
- 238000000034 method Methods 0.000 abstract 1
- 238000009434 installation Methods 0.000 description 19
- 238000013461 design Methods 0.000 description 10
- 230000007547 defect Effects 0.000 description 4
- 230000009466 transformation Effects 0.000 description 3
- 230000003044 adaptive effect Effects 0.000 description 2
- 239000002826 coolant Substances 0.000 description 2
- 238000001816 cooling Methods 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000007796 conventional method Methods 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000000314 lubricant Substances 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 239000010705 motor oil Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 239000010729 system oil Substances 0.000 description 1
- 238000010998 test method Methods 0.000 description 1
- 230000003245 working effect Effects 0.000 description 1
Images
Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Testing Of Engines (AREA)
Abstract
The application belongs to the technical field of engine tests, and particularly relates to a turboprop aircraft outer lubricating oil system and engine ground rack joint test device. The device comprises an engine mounting rack (8), the engine mounting rack (8) fixedly supports an engine (3) and a lubricating oil tank (6) through an engine mounting pull rod (7), a nacelle lower cover (11) is fixedly supported through a nacelle support rod (10), the front end of the nacelle lower cover (11) is connected with a nacelle front section (2), the engine (3) is located in the nacelle lower cover (11), an output shaft of the engine (3) penetrates through the nacelle front section (2) to be connected with a propeller (1), a radiator exhaust passage (16) is arranged on the nacelle front section (2) and the nacelle lower cover (11), a lubricating oil radiator (17) is arranged in the radiator exhaust passage (16), and the lubricating oil radiator (17) is connected with the lubricating oil tank (6) and the engine (3). The method and the device can smoothly realize the full physical state simulation of the external lubricating oil system, and complete the joint test with the engine ground rack.
Description
Technical Field
The application belongs to the technical field of engine tests, and particularly relates to a turboprop aircraft outer lubricating oil system and engine ground rack joint test device.
Background
Currently, aviation turbofan and turbojet engines are usually equipped with an integrated lubrication system, and the cooling of the lubricant is realized by a lubricant-burning radiator, and the fuel is used as a cooling medium. The turboprop engine generally adopts outside air as a cooling medium to carry out oil cooling, and an oil system arranged on an aircraft to ensure the turboprop engine to normally work is called an external oil system. The external oil system typically includes components such as a radiator, an oil sump, a breather tank, an oil temperature sensor, and an oil slide. The components need to be orderly combined and then matched with the performance of the engine body so as to ensure the normal and stable operation of the engine. Because of the complexity of the system oil circuit and the strong coupling between the working components, how to verify the functional performance of the external lubricating oil system is a difficult point of the design of the aircraft power plant system, the actual state of the matching work of the system and the engine cannot be completely reflected according to the conventional method only depending on component test and performance simulation, and the defect that the system does not meet the design requirement after being installed is easily caused. The development of the full-state test of the installation machine faces a plurality of difficulties in the design stage and is difficult to realize.
Disclosure of Invention
In order to solve the technical problem, the application provides a turboprop aircraft outer lubricating oil system and engine ground rack joint test device, a test model is built in a full physical state, a ground test bed based on an engine development side is used for carrying out adaptive technology transformation and upgrading, all relevant parts of the outer lubricating oil system are installed according to the installation state of an aircraft, important performance parameters of the system are measured, the engine is driven according to the use working condition, the full state joint test of the outer lubricating oil system and the engine is realized, the working states of the engine and the outer lubricating oil system are monitored, the installation performance of the system is verified, and various feedbacks of the system to the engine are correctly evaluated.
The utility model provides an outer lubricating oil system of turboprop aircraft and engine ground rack antithetical couplet examination device, including the engine installation rack, the engine installation rack passes through engine installation pull rod fixed stay engine and lubricating oil case, the engine installation rack covers under passing through nacelle bracing piece fixed stay nacelle, the cover front end is connected with the nacelle anterior segment under the nacelle, the engine is located the cover under the nacelle, the output shaft of engine passes the nacelle anterior segment and connects the screw, wherein, cover under nacelle anterior segment and the nacelle and be provided with the radiator exhaust passage, be provided with the lubricating oil radiator in the radiator exhaust passage, the lubricating oil radiator with lubricating oil case and engine are connected, the radiator exhaust passage is opened at the nacelle front end has lubricating oil radiator air intake, cover rear end is provided with radiator exhaust air door under the nacelle.
Preferably, the lubricating oil radiator is connected with the engine through a lubricating oil hose, and the engine is connected with the lubricating oil tank through the lubricating oil hose.
Preferably, the oil tank is further connected to the breather tank through an oil hose.
Preferably, the rear end of the radiator exhaust passage is provided with a wind force measuring rod, the wind force measuring rod is connected with an air door electric mechanism, and the air door electric mechanism is used for controlling the opening of an air door to realize the flow control of the radiator exhaust passage.
Preferably, the front end of the exhaust air door of the radiator is provided with an angular displacement sensor of the air door rotating shaft.
Preferably, the radiator exhaust passage is provided with a pressure sensor at the front end of the lubricating oil radiator.
Preferably, the radiator exhaust passage is provided with a pressure sensor and a temperature sensor at the rear end of the lubricating oil radiator.
Preferably, the oil hose is provided with a flow meter and a temperature sensor.
Preferably, the external lubricating oil system is provided with a control box or a computing device filled with temperature control software.
Preferably, the selection of the starting time of the engine bench test comprising the ground bench combined test device comprises the time of a high-temperature environment in hot days.
The application carries out limited technological transformation on the basis that the engine has the ground test bed, can realize the full physical state test of outer lubricating oil system to verify insufficient current situation before changing outer lubricating oil system design installation, avoid unsatisfied design demand's defect behind the outer lubricating oil system installation. Engineering practices prove that the external lubricating oil system and engine ground rack joint test device can smoothly realize the full physical state simulation of the external lubricating oil system and complete the joint test with the engine ground rack.
Drawings
Fig. 1 is a schematic structural diagram of a preferred embodiment of the turboprop aircraft external lubricating oil system and engine ground bench combined test device of the present application.
Fig. 2 is a perspective view of the embodiment of fig. 1 of the present application.
The system comprises a propeller 1, a nacelle 2, an engine 3, an oil hose 4, a breather box 5, an oil tank 6, an engine installation pull rod 7, an engine installation rack 8, an engine exhaust pipe 9, a nacelle support rod 10, a nacelle lower cover 11, an air door force measuring rod 12, a radiator exhaust air door 13, an air door rotating shaft angular displacement sensor 14, an air door electric mechanism 15, a radiator exhaust passage 16, an oil radiator 17 and an oil radiator air inlet 18.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all embodiments of the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application, and should not be construed as limiting the present application. All other embodiments obtained by a person of ordinary skill in the art without any inventive work based on the embodiments in the present application are within the scope of protection of the present application. Embodiments of the present application will be described in detail below with reference to the drawings.
The application provides a turboprop aircraft outer lubricating oil system and engine ground rack antithetical couplet examination device to comprehensively systematically verify outer lubricating oil system and engine matching working property, eliminate the defect that unsatisfied design demand after the system installation.
The tested piece (equipment or part) of the application should contain the lubricating oil radiator, the lubricating oil tank, the vent box, the lubricating oil pump, the lubricating oil temperature sensor, the cold edge air inlet and outlet channel of the radiator and the lubricating oil pipeline (a hose and a hard pipe) of an outer lubricating oil system. The installation should be arranged at engine test bench according to the installed position of design (for the engine) by the test piece, should contain the engine of holostate by the test piece, the turboprop engine should be equipped with the screw of installed state, experimental measurement and control equipment should contain the temperature sensor who installs additional, pressure sensor, the flowmeter, angular displacement sensor and dynamometry pole, survey when experimental and get lubricating oil circulation flow, lubricating oil pump entry oil pressure oil temperature, radiator access & exit oil pressure oil temperature, radiator cold side passageway is imported and exported air current temperature, accompany the test piece and should contain the radiating organism structure of influence lubricating oil, including nacelle anterior segment and middle section. Based on this, the turboprop aircraft outer lubricating oil system and engine ground rack antithetical couplet examination device that this application provided, as shown in fig. 1 and fig. 2, mainly include:
the engine installation rack 8 is characterized in that the engine installation rack 8 fixedly supports an engine 3 and a lubricating oil tank 6 through an engine installation pull rod 7, the engine installation rack 8 fixedly supports a lower nacelle cover 11 through a nacelle support rod 10, the front end of the lower nacelle cover 11 is connected with a front nacelle section 2, the engine 3 is located in the lower nacelle cover 11, an output shaft of the engine 3 penetrates through the front nacelle section 2 and is connected with a propeller 1, a radiator exhaust passage 16 is arranged on the front nacelle section 2 and the lower nacelle cover 11, a lubricating oil radiator 17 is arranged in the radiator exhaust passage 16, the lubricating oil radiator 17 is connected with the lubricating oil tank 6 and the engine 3, an air inlet 18 of the lubricating oil radiator is formed in the front end of the nacelle through the radiator exhaust passage 16, and a radiator exhaust air door 13 is arranged at the rear end of the lower nacelle cover 11.
The system is based on an engine ground test bed, adaptive technology upgrading and transformation are carried out, a related structure of an airplane cabin body is assembled, all related equipment and components of an outer lubricating oil system are installed according to the installation state of the airplane, test equipment for parameters such as temperature, pressure and flow is additionally installed, the engine is driven according to a set working condition, the all-state joint test of the outer lubricating oil system and the engine is achieved, the working states of the engine and the outer lubricating oil system are monitored, and important performance parameters of the system are measured and obtained so as to verify and evaluate the installation performance of the system. The test method has reliable technical principle and stronger engineering feasibility. The test can avoid the defect that the system does not meet the design requirement after being installed.
In some alternative embodiments, the oil radiator 17 is connected to the engine 3 through an oil hose 4, and the engine 3 is connected to the oil tank 6 through the oil hose 4.
In some alternative embodiments, the oil tank 6 is also connected to the breather tank 5 by an oil hose 4.
In some optional embodiments, a wind force measuring rod 12 is arranged at the rear end of the radiator exhaust passage 16, the wind force measuring rod 12 is connected with a throttle electric mechanism 15, and the throttle electric mechanism 15 is used for controlling the opening degree of a throttle to realize the flow control of the radiator exhaust passage 16.
In some alternative embodiments, the front end of the radiator exhaust air damper 13 is provided with a damper rotating shaft angular displacement sensor.
In some alternative embodiments, the radiator outlet 16 is provided with a pressure sensor at the front end of the oil radiator 17.
In some alternative embodiments, the radiator exhaust duct 16 is provided with a pressure sensor and a temperature sensor at the rear end of the oil radiator 17.
In some optional embodiments, a flow meter and a temperature sensor are arranged on the oil hose 4.
In some alternative embodiments, the external oil system is equipped with a control box or computing device that is filled with temperature control software.
In this embodiment, for an external lubricating oil system with an automatic lubricating oil temperature control function, the tested piece should include a control box or other computing equipment filled with temperature control software.
In some alternative embodiments, the selection of the engine bench test start-up timing comprising the ground bench joint test device comprises a hot-day high-temperature environment timing to fully verify the harsh working environment of the external lubricating oil system.
The test result of the embodiment shows that under typical ground working conditions, the working state of the engine is stable, the monitored important parameters of the outer lubricating oil system and the engine body are in the range of design requirements, and the system and the engine are effectively verified, so that reliable data support is provided for the design of a rotary section.
The above description is only for the specific embodiments of the present application, but the scope of the present application 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 application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (10)
1. A turboprop aircraft external lubricating oil system and engine ground bench combined test device is characterized by comprising an engine mounting bench (8), wherein the engine mounting bench (8) fixedly supports an engine (3) and a lubricating oil tank (6) through an engine mounting pull rod (7), the engine mounting bench (8) fixedly supports a lower nacelle cover (11) through a nacelle support rod (10), the front end of the lower nacelle cover (11) is connected with a front nacelle section (2), the engine (3) is positioned in the lower nacelle cover (11), an output shaft of the engine (3) penetrates through the front nacelle section (2) to be connected with a propeller (1), radiator exhaust passages (16) are arranged on the front nacelle cover (2) and the lower nacelle cover (11), a lubricating oil radiator (17) is arranged in the radiator exhaust passages (16), and the lubricating oil radiator (17) is connected with the lubricating oil tank (6) and the engine (3), the front end of the exhaust passage (16) of the radiator is provided with an air inlet (18) of the lubricating oil radiator, and the rear end of the lower cover (11) of the nacelle is provided with an exhaust air door (13) of the radiator.
2. The turboprop aircraft external lubricating oil system and engine ground bench test united device of claim 1, characterized in that the lubricating oil radiator (17) is connected with the engine (3) through a lubricating oil hose (4), and the engine (3) is connected with the lubricating oil tank (6) through the lubricating oil hose (4).
3. The turboprop external lubrication system and engine floor skid joint test apparatus according to claim 2, wherein the lubricating oil tank (6) is further connected to the breather tank (5) through a lubricating oil hose (4).
4. The turboprop aircraft external lubricating oil system and engine ground rack combined test device according to claim 1, wherein a wind force measuring rod (12) is arranged at the rear end of the radiator exhaust passage (16), the wind force measuring rod (12) is connected with a throttle electric mechanism (15), and the throttle electric mechanism (15) is used for controlling the opening degree of a throttle to realize the flow control of the radiator exhaust passage (16).
5. The turboprop aircraft external lubricating oil system and engine ground rack joint test device of claim 4, characterized in that the front end of the radiator exhaust air damper (13) is provided with an air damper rotating shaft angular displacement sensor.
6. The turboprop aircraft external oil lubrication system and engine ground skid joint test apparatus according to claim 1, wherein the radiator exhaust passage (16) is provided with a pressure sensor at a front end of the oil radiator (17).
7. The turboprop aircraft external lubricating oil system and engine ground rack joint test device according to claim 1, characterized in that the radiator exhaust duct (16) is provided with a pressure sensor and a temperature sensor at the rear end of the lubricating oil radiator (17).
8. The turboprop aircraft external lubricating oil system and engine ground rack joint test device according to claim 1, characterized in that a flow meter and a temperature sensor are arranged on the lubricating oil hose (4).
9. The turboprop external lubrication system and engine floor skid joint test apparatus according to claim 1, wherein the external lubrication system is equipped with a control box or a computing device filled with temperature control software.
10. The turboprop aircraft external lubricating oil system and engine ground bench joint test apparatus of claim 1, wherein the selection of the start time of the engine bench test comprising the ground bench joint test apparatus comprises the time of a hot day high temperature environment.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111641463.2A CN114486276A (en) | 2021-12-29 | 2021-12-29 | Turboprop aircraft outer lubricating oil system and engine ground rack joint test device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111641463.2A CN114486276A (en) | 2021-12-29 | 2021-12-29 | Turboprop aircraft outer lubricating oil system and engine ground rack joint test device |
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| CN114486276A true CN114486276A (en) | 2022-05-13 |
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2021
- 2021-12-29 CN CN202111641463.2A patent/CN114486276A/en active Pending
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Application publication date: 20220513 |