CN205280367U - Aeroengine combustion chamber performance test is with encircling displacement mechanism entirely - Google Patents
Aeroengine combustion chamber performance test is with encircling displacement mechanism entirely Download PDFInfo
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- CN205280367U CN205280367U CN201521047430.5U CN201521047430U CN205280367U CN 205280367 U CN205280367 U CN 205280367U CN 201521047430 U CN201521047430 U CN 201521047430U CN 205280367 U CN205280367 U CN 205280367U
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Abstract
The utility model relates to an aeroengine combustion chamber performance test is with encircling displacement mechanism entirely. Comprise casing 1 and rotatable parts 2 two parts, casing 1 supports rotatable parts 2 and constitutes airflow channel, and rotatable parts 2 drives installation test on it and receives 4 rotations in the sense portion to reach the mesh of measuring combustion chamber outlet flow parameter. Casing 1 adopts the water -cooling, and rotatable parts 2 adopts air cooling, and cooling gas direct aperture from displacement mechanism front end and radial anchor ring through the rotatable parts 2 inside passage heat transfer after enters the surface temperature of the modern combustion chamber wall cooling technique of gas through adopting " impacts + convection current + air film " with reduction and gas direct contact parts. Rotatable parts 2 adopts the vice kind of drive of reversing gear, and 4 different kinds of tests of mountable receive sense portion 4 on the part, and every test receives sense portion 4 to have special cooling water passageway supply cooling water. The utility model overcomes the problem that current displacement mechanism performance index is low, the structure is complicated, the fault rate is high, the commonality is poor.
Description
Technical field
The present invention is applied to performance test field, aeroengine combustor buring room, is especially applicable to aeroengine combustor buring room outlet parameter and measures.
Background technology
Aeroengine combustor buring room performance test loopful displacement mechanism is the important tests equipment of combustor test, is the important technical obtaining combustor exit parameter. Under the trend that engine chamber outlet temperature pressure develops to increasingly higher direction, the high-performance displacement mechanism great significance for design to combustor.
Domestic most representational loopful displacement mechanism (624 institute) is the design of the initial stage eighties, processing at present, through the use of more than 20 years, this displacement mechanism serious aging, hydraulic performance decline, its design objective, frame mode can not meet current higher performance first class engine combustor test demand. (design temperature of original displacement mechanism is 1650K, and the mean temperature of engine chamber outlet at present is up to 1850K). Therefore, for meeting the development of high-performance enginer combustor, redesign processing large-scale loopful displacement mechanism of new generation extremely urgent.
Summary of the invention
Goal of the invention: provide a kind of aeroengine combustor buring room performance test loopful displacement mechanism, overcomes that existing displacement mechanism performance indications are low, structure is complicated, fault rate is high, the problem of poor universality.
A kind of aeroengine combustor buring room performance test loopful displacement mechanism of the present invention is mainly the guarantee condition that high-performance combustor development provides necessary, meets the requirement of high-performance enginer chamber performance test.
This displacement mechanism is mainly made up of housing (1) and rotatable parts (2) two parts, housing (1) plays support rotating parts (2) and constitutes the effect of gas channel, rotatable parts (2) drive the test detector probe (4) being mounted above to rotate by driving device (3), to reach to measure the purpose of combustor exit flow parameter. Housing (1) adopts water-cooled, and cooling water flows in the interlayer of housing (1), discharges from special water stream channel after taking away the heat of wall. Rotatable parts (2) adopt air cooling, cooling gas directly enters combustion gas from displacement mechanism front end (close combustor end) and the aperture of radial direction anchor ring (being equivalent to combustor exit passage internal ring overall diameter) after by rotatable parts (2) inner passage heat exchange, to reduce the surface temperature (by adopting the modern combustion chambers wall cooling technology surface temperature with reduction and the direct contact component of combustion gas of " impact+convection current+air film ") with the direct contact component of combustion gas. Being connected by screw between housing (1) and rotatable parts (2), the sealing between rotatable parts (2) adopts the middle method adding oiliness bearing (20) and O-shaped rubber ring (21) to solve. Can installing 4 different types of test detector probes (4) on rotatable parts (2), every test detector probe (4) has special cooling-water duct cooling water supply to cool down. Meanwhile, consider the versatility of displacement mechanism when design, the rotor (18) in rotatable parts (2) is designed to dismountable two sections, can be replaced according to the physical dimension of different combustor.
Accompanying drawing explanation
Fig. 1 displacement mechanism structure is always schemed
Fig. 2 displacement mechanism housing (1) structural representation
Fig. 3 displacement mechanism rotatable parts (2) structural representation
Wherein, housing-1; Rotatable parts-2; Driving device-3; Test detector probe-4; Shell body-5; Inner housing-6; Rear water-cooled lid-7; Water collar-8; Upper cover-9; Lower cover-10; Compensating wire outlet-11; Combustion gas probe tube outlet-12; The air inlet-13 of cooling gas; Pressure fairlead-14; Cooling water inlet/outlet pipe outlet-15; Fixture-16; Drive disk assembly-17; Rotor-18; Measurement apparatus dish-19; Oiliness bearing-20; O-shaped rubber ring-21; Power transmission shaft-22; Commutation bevel gear-23; Canine tooth wheel disc-24; Detector probe mounting disc-25; Location separator-26; Pressure monitoring pipe-27; Cooling water circulation passage-28; Four intake tunnels-29; Film cooling holes-30; Rolling bearing-31; Four exhalant canals-32.
Beneficial effect
Instant invention overcomes that existing displacement mechanism performance indications are low, structure is complicated, fault rate is high, the problem of poor universality. It is mainly the guarantee condition that high-performance combustor development provides necessary, meets the requirement of high-performance enginer chamber performance test.
Detailed description of the invention
As shown in Figure 1 to Figure 3, the concrete constituted mode of various piece of the present invention is as follows:
1, housing (1)
Housing (1) is divided into shell body (5), inner housing (6), rear water-cooled lid (7), water collar (8), upper cover (9) and lower cover (10). Displacement mechanism housing (1), owing to directly contacting with high-temperature fuel gas, therefore adopts water-cooling structure. Water-cooling structure is divided into two passages: water-cooling structure passes on left rear water-cooled cap-shaped and becomes a passage, forms a passage by water collar on the right side of water-cooling structure. Adopt sandwich design, interlayer intermediate formation cooling water stream channel between housing shell body (5) and inner housing (6), be high-temperature fuel gas circulation road outside interlayer, be cooling air flow passage inside interlayer. Passage inside interlayer still tests detector probe (4) compensating wire and combustion gas probe tube extraction channel simultaneously. Housing (1) two ends are connected with combustor with testing equipment respectively. Driving device (3) and power transmission shaft (22) are coupled together by upper cover (9), its design has test detector probe (4) compensating wire outlet (11) and combustion gas probe tube outlet (12), is also configured with the air inlet (13) of cooling gas simultaneously. Lower cover design has test detector probe (4) pressure fairlead (14) and cooling water inlet/outlet pipe outlet (15). Separately below housing (1) major part structure is illustrated.
A) shell body (5) and inner housing (6)
Shell body (5) and inner housing (6) are the bases of whole displacement mechanism, and it defines cooling water and the cooling air flow passage of displacement mechanism, and plays a part to connect displacement mechanism rotatable parts (2).
B) water-cooled lid (7) afterwards
Rear water-cooled lid (7) makes cooling current in housing (1) left side form a complete passage. Inner housing (6) rear end is blocked and is made cooling air flow direction test detector probe (4) root by rear water-cooled lid (7).
C) water collar (8)
Water collar (8) makes cooling current in housing (1) right side form a complete circulation.
D) upper cover (9) and lower cover (10)
Upper cover (9) and lower cover (10) are the outlets of test detector probe (4) manometer tube and compensating wire, and driving device (3) and power transmission shaft (22) are coupled together and drive whole rotatable parts (2) to rotate by upper cover (9). Upper cover (9) still cools down the import of gas simultaneously. Lower cover (10) still tests the connector that detector probe (4) is cooling water circulation simultaneously.
2, rotatable parts (2)
Rotatable parts (2) are divided into fixture (16), drive disk assembly (17), rotor (18) and measurement apparatus dish (19). Drive disk assembly (17), rotor (18) and measurement apparatus dish (19) are coupled together by standing part, are sealed by oiliness bearing (20) and O-shaped rubber ring (21) between fixture (16) and rotor (18); Drive disk assembly (17) is made up of a power transmission shaft (22), commutation bevel gear (23) and canine tooth wheel disc (24). Rotor (18) designs the passage that promising test detector probe (4) provides cooling water circulation; Measurement apparatus dish (19) is made up of detector probe mounting disc (25) and location separator (26), can installing 4 different types of test detector probes (4) in detector probe mounting disc (25), location separator (26) solves orientation problem when displacement mechanism is installed with combustion box and plays a part blanking cover (being separated by the passage inside high-temperature fuel gas stream and housing (1) interlayer). In order to ensure that air cooling pressure is more than gaseous-pressure, devise pressure monitoring pipe (27), monitored air cooling pressure and gaseous-pressure by pressure comparison.
Separately below rotatable parts (2) primary structure is illustrated.
A) fixture (16)
Drive disk assembly (17), rotor (18) and measurement apparatus dish (19) are coupled together by fixture (16). Fixture (16) collectively forms sealing structure by oiliness bearing (20) and 0 type rubber ring (21) with rotor (18).
B) drive disk assembly (17)
Drive disk assembly (17) is made up of a power transmission shaft (22), commutation bevel gear (23) and canine tooth wheel disc (24). Power transmission shaft (22) is connected with driving device (3) by a shaft joint, power transmission shaft (22) drives commutation bevel gear (23) to rotate, and commutation bevel gear (23) drives canine tooth wheel disc (24) to rotate.
C) rotor (18)
Rotor (18) is connected with canine tooth wheel disc (24) by screw, is connected with detector probe mounting disc (25) by screw thus driving test detector probe (4) to rotate to obtain measurement parameter. Rotor (18) medium design has test detector probe (4) cooling water circulation passage (28) (two annular tracts), test detector probe (4) water inlet is divided into four intake tunnels (29) by an annular tract, and test detector probe (4) water outlet is divided into four exhalant canals (32) also by an annular tract. Rotor (18) is designed to hollow structure, in order to the extraction of parameter is measured in test detector probe (4).
D) measurement apparatus dish (19)
Measurement apparatus dish (19) is made up of detector probe mounting disc (25) and location separator (26). Can installing 4 different types of test detector probes (4) in detector probe mounting disc (25) circumference, location separator (26) solves orientation problem when displacement mechanism is installed with combustion box and plays a part blanking cover (high-temperature fuel gas stream and air cooling passage being separated). Test detector probe (4) is connected with detector probe mounting disc (25) by screw. The upper anchor ring contacted with high-temperature fuel gas in location separator (26) has film cooling holes (30), by adopting the modern combustion chambers wall cooling technology surface temperature with reduction with combustion gas direct contact component location dish of " impact+convection current+air film "; Considering that cooling gas is on thermometric impact, film cooling holes (30) tilts certain angle along the direction of combustion gas stream, and thermometric impact is preferably minimized by cooling gas.
3, transmission
The transmission of displacement mechanism rotatable parts (2) is the key that whole displacement mechanism measures parameter acquiring. Transmission realizes mainly through power transmission shaft (22), commutation bevel gear (23) and canine tooth wheel disc (24). The design of transmission mainly considers to reduce moment of friction and rotary inertia. For this, contact with each other partial design rolling bearing (31) at canine tooth wheel disc (24), rotor (18), standing part (16). The use of this rolling bearing (31) makes moment of friction and rotary inertia be greatly reduced, and the rotation of displacement mechanism becomes to be more prone to, and becomes much larger in the range of choice of driving device (3).
Claims (4)
1. an aeroengine combustor buring room performance test loopful displacement mechanism, it is characterized in that, overall structure includes housing (1) and rotatable parts (2), and housing (1) is divided into shell body (5), inner housing (6), rear water-cooled lid (7), water collar (8), upper cover (9) and lower cover (10); Housing (1) support rotating parts (2) also constitute gas channel, and rotatable parts (2) drive the test detector probe (4) being mounted above to rotate, to measure combustor exit flow parameter; Housing (1) adopts water-cooling structure, and cooling water flows in the interlayer of housing (1), discharges from special water stream channel after taking away the heat of wall; Housing (1) two ends are connected with combustor with testing equipment respectively; Driving device and power transmission shaft are coupled together by upper cover (9), and lower cover design has test detector probe (4) pressure fairlead (14) and parameter measurement rake cooling water inlet/outlet pipe outlet (15);
Rotatable parts (2) are divided into fixture (16), drive disk assembly (17), rotor (18) and measurement apparatus dish (19); Rotatable parts (2) adopt air cooling, and cooling gas directly enters combustion gas from the film cooling holes (30) of displacement mechanism front end and radial direction anchor ring after by rotatable parts (2) inner passage heat exchange; Drive disk assembly (17), rotor (18) and measurement apparatus dish (19) are coupled together by fixture (16), are sealed by oiliness bearing (20) and O-shaped rubber ring (21) between fixture (16) and rotor (18); Drive disk assembly (17) is made up of a power transmission shaft (22), commutation bevel gear (23) and canine tooth wheel disc (24); Rotor arranges the passage that promising test detector probe (4) provides cooling water circulation; Measurement apparatus dish (19) is made up of measurement rake mounting disc (25) and location separator (26), rotatable parts (2) adopt the kind of drive of commutating tooth wheel set, can installing 4 different types of test detector probes (4) on parts, every test detector probe (4) is provided with cooling-water duct cooling water supply; Rotor includes dismountable two sections: detector probe mounting disc (25) and location separator (26), can be replaced according to the physical dimension of different combustor; Rotatable parts (2) are additionally provided with pressure monitoring pipe (27), are monitored air cooling pressure and gaseous-pressure by pressure comparison.
2. a kind of aeroengine combustor buring room as claimed in claim 1 performance test loopful displacement mechanism, it is characterized in that, described water-cooling structure includes two passages: housing (1) passes on left rear water-cooled lid (7) and forms a passage, housing (1) right side forms a passage by water collar (8), housing (1) adopts sandwich design, interlayer intermediate formation cooling water stream channel, it is high-temperature fuel gas circulation road outside interlayer, is cooling air flow passage inside interlayer.
3. a kind of aeroengine combustor buring room as claimed in claim 1 performance test loopful displacement mechanism, it is characterized in that, described canine tooth wheel disc (24), rotor (18), fixture (16) part that contacts with each other adopts rolling bearing (31) structure reducing moment of friction.
4. a kind of aeroengine combustor buring room as claimed in claim 1 performance test loopful displacement mechanism, it is characterized in that, described rotor (18) is hollow structure, being connected with canine tooth wheel disc (24) by screw, being connected with detector probe mounting disc (25) by screw thus driving test detector probe (4) to rotate to obtain measurement parameter; Rotor medium design has test detector probe (4) cooling water circulation passage (28), structure is two annular tracts, test detector probe (4) water inlet is divided into four intake tunnels (29) by an annular tract, and test detector probe (4) water outlet is divided into four exhalant canals (32) also by an annular tract.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521047430.5U CN205280367U (en) | 2015-12-15 | 2015-12-15 | Aeroengine combustion chamber performance test is with encircling displacement mechanism entirely |
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| CN201521047430.5U CN205280367U (en) | 2015-12-15 | 2015-12-15 | Aeroengine combustion chamber performance test is with encircling displacement mechanism entirely |
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| CN205280367U true CN205280367U (en) | 2016-06-01 |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111550569A (en) * | 2020-04-22 | 2020-08-18 | 中国科学院力学研究所 | Opening and closing device suitable for combustion chamber |
| CN112423554A (en) * | 2020-11-20 | 2021-02-26 | 常州工学院 | Water cooling device for data acquisition sensor of rotary combustion chamber |
| CN113739939A (en) * | 2021-08-31 | 2021-12-03 | 中国航发贵阳发动机设计研究所 | Total temperature probe for outlet of combustion chamber |
| CN117990381A (en) * | 2024-04-03 | 2024-05-07 | 成都晨发泰达航空科技股份有限公司 | Test device for simulating and verifying aeroengine combustion chamber aerodynamic performance |
-
2015
- 2015-12-15 CN CN201521047430.5U patent/CN205280367U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111550569A (en) * | 2020-04-22 | 2020-08-18 | 中国科学院力学研究所 | Opening and closing device suitable for combustion chamber |
| CN112423554A (en) * | 2020-11-20 | 2021-02-26 | 常州工学院 | Water cooling device for data acquisition sensor of rotary combustion chamber |
| CN113739939A (en) * | 2021-08-31 | 2021-12-03 | 中国航发贵阳发动机设计研究所 | Total temperature probe for outlet of combustion chamber |
| CN117990381A (en) * | 2024-04-03 | 2024-05-07 | 成都晨发泰达航空科技股份有限公司 | Test device for simulating and verifying aeroengine combustion chamber aerodynamic performance |
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Address after: 610500 Xindu Xuefu Road, Xindu District, Chengdu, Sichuan Patentee after: AECC SICHUAN GAS TURBINE Research Institute Address before: 621703 operation monitoring department, mailbox 305, Jiangyou, Sichuan, Mianyang, Sichuan Patentee before: CHINA GAS TURBINE EST |
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| CP03 | Change of name, title or address |