Nozzle purge pressure measuring device

Abstract

The nozzle purging pressure measuring device comprises a test section cylinder body and a nozzle test piece, and the test section cylinder body comprises an air flow chamber; the nozzle test piece is arranged at the downstream of the test section cylinder and communicated with the air flowing chamber, the nozzle test piece comprises a swirler, a shell, an end cover and an oil collecting ring, the shell is located in the swirler, an annular gap is defined by the shell and the swirler, the shell comprises a first hole part, and the first hole part is communicated with the annular gap; the end cover is located in the shell and comprises an inner circumferential cavity and a second hole part communicated with the inner circumferential cavity. The oil collecting ring comprises a pressure collecting hole, a third hole part and a fourth hole part, the fourth hole part is communicated with the second hole part and the first hole part, the third hole part is communicated with the pressure collecting hole and the first hole part, and the pressure collecting hole is used for collecting the pressure of the third hole part. The device can effectively measure the purging pressure.

Description

TECHNICAL FIELD

[0001] The utility model relates to the test field of aero-engine, specifically relates to the test component field of nozzle. BACKGROUND

[0002] The fuel in the fuel nozzle of the combustion chamber is heated by the convection of air from the compressor and the convection radiation of the flame in the combustion chamber, and is easy to deposit and coking on the wall surface of the oil way. In order to ensure that the fuel in the oil way does not coking, the main oil way of the fuel nozzle is usually designed with a purge structure at each main nozzle. In order to verify the purging effect of the fuel in the oil way, a purge pressure measuring device is needed. SUMMARY

[0003] An object of the utility model is to provide a nozzle purge pressure measuring device, which can effectively measure the purge pressure.

[0004] To achieve the above-mentioned purpose of nozzle purge pressure measuring device includes test section cylinder and nozzle test piece, test section cylinder includes air flow chamber;The nozzle test piece is arranged downstream of the test section cylinder, and is communicated with the air flow chamber, the nozzle test piece includes vortex generator, shell, end cover, oil collecting ring, the shell is located inside the vortex generator, and the vortex generator is surrounded by the annular gap, including first hole part, the first hole part communicates the annular gap;The end cover is located inside the shell, including inner peripheral chamber and second hole part communicated with the inner peripheral chamber;The oil collecting ring is located at the end of the end cover along the airflow direction, and is located inside the shell, including pressure collection hole, third hole part and fourth hole part, the fourth hole part is communicated with the second hole part, the first hole part, the third hole part is communicated with the pressure collection hole, the first hole part, the pressure collection hole is used to collect the pressure of the third hole part.

[0005] In one or more embodiments, a boss is arranged on the oil collecting ring and abuts against the shell, and the third hole part is arranged on the boss.

[0006] In one or more embodiments, the axis of the pressure collection hole is parallel to the axis of the test section cylinder.

[0007] In one or more embodiments, the fourth hole part and the third hole part pressure collection hole are arranged circumferentially staggered.

[0008] In one or more embodiments, the oil collecting ring includes a shell bayonet, the shell bayonet abuts against the inner wall of the shell, and a circumferentially distributed first sealing ring is further arranged between the oil collecting ring and the shell.

[0009] In one or more embodiments, an annular gap is arranged between the axial end of the end cover and the axial end of the oil collecting ring, and the annular gap is communicated with the first hole part and the second hole part.

[0010] In one or more embodiments, an end of the end cap in the direction of gas flow includes a radially-contracted shoulder, the oil slinger is provided with a groove that accommodates the shoulder, and the shoulder and the groove are in axial sealing engagement.

[0011] In one or more embodiments, an end of the end cap opposite the end in the direction of gas flow includes an end cap connecting flange, an end of the housing opposite the end in the direction of gas flow includes a housing connecting flange, and the end cap connecting flange, the housing connecting flange, and an end of the swirler are secured by a connector.

[0012] In one or more embodiments, the device further includes a pressure acquisition device in communication with the pressure acquisition hole.

[0013] In one or more embodiments, the swirler is provided with a fifth hole portion in communication with the annular gap.

[0014] The nozzle blow-by pressure measurement device described above uses the third hole portion as the main nozzle, uses the pressure acquisition device to acquire the main nozzle pressure data obtained by the pressure acquisition hole in real time, so that the blow-by capacity of the fuel nozzle can be verified in advance by the nozzle test piece. BRIEF DESCRIPTION OF DRAWINGS

[0015] The above and other features, properties, and advantages of the present utility model will become more apparent through the following description with reference to the accompanying drawings and embodiments, in which:

[0016] Figure 1 is an oblique view of a nozzle blow-by pressure measurement device;

[0017] Figure 2 is a top view of a nozzle blow-by pressure measurement device

[0018] Figure 3 is a sectional view of a nozzle blow-by pressure measurement device along the A-A direction;

[0019] Figure 4 is an oblique view of a nozzle test piece;

[0020] Figure 5 is a side view of a nozzle test piece;

[0021] Figure 6 is a right view of a nozzle test piece;

[0022] Figure 7 is a sectional view along the B-B direction;

[0023] Figure 8 is Figure 7 is an enlarged view of C in FIG. 6;

[0024] Figure 9 is a sectional view along the direction of D-D;

[0025] Figure 10 is Figure 9 is an enlarged view at E in

[0026] Figure 11 is an assembly view of the nozzle test piece. DETAILED DESCRIPTION

[0027] The utility model will be further described below in combination with specific embodiments and drawings, and more details are set forth in the following description so as to fully understand the utility model, but the utility model can obviously be implemented in various other ways different from the description, and those skilled in the art can make similar generalization and deduction according to actual application conditions without departing from the connotation of the utility model, therefore the protection scope of the utility model should not be limited by the content of the specific embodiments.

[0028] It should be noted that these and other subsequent drawings are merely examples, are not drawn according to the condition of the same scale, and should not be used as a limitation on the protection scope actually required by the utility model.

[0029] The aero-engine fuel nozzle is mainly affected by the convective heat transfer from the high-pressure compressor outlet air and the radiative heat transfer from the combustion gas in the flame tube in the combustion chamber. With the increase of the combustion chamber inlet temperature, the oil passage wall temperature in the fuel nozzle and the fuel temperature are also continuously increased. Higher fuel wet wall temperature makes the fuel react with the oxygen dissolved therein and deposit and coking on the oil passage wall surface, reduces the flow area of the fuel pipeline, and even blocks the nozzle in severe cases, affecting the fuel atomization effect. The deteriorated fuel atomization effect will lead to the deterioration of the combustion efficiency, emission, outlet temperature distribution of the combustion chamber, the increase of the oil consumption of the engine, the decline of the power performance, and the difficulty in guaranteeing the working life of the turbine blade, which seriously threatens the flight safety. Therefore, it is necessary to take thermal protection measures for the nozzle to reduce the heating effect of the external heat source on the fuel, so as to avoid the occurrence of coking phenomenon.

[0030] The following measures exist at present to reduce the coking of the fuel nozzle. For example, the nozzle is cooled by air or fuel; or the structure outside the fuel pipeline is designed to reduce heat exchange; or the fuel passage geometry and thermal protection design are improved to reduce the wet wall temperature; or the surface of the fuel passage is treated to inhibit carbon deposition.

[0031] For the main combustion stage oil circuit, the remaining fuel in the oil circuit after the main combustion stage oil circuit is closed needs to be purged. The structure design is such that the pressure of part of the main injection ports is greater than that of the remaining main injection ports, and air enters the main combustion stage oil circuit from the main injection ports with greater pressure, blowing the main combustion stage fuel out of the main injection ports with smaller pressure. To ensure the purging effect of the main combustion stage oil circuit, after the purging structure design is completed, the purging effect of the fuel in the main combustion stage oil circuit needs to be tested and verified. One of the measurement standards for the purging effect is the difference in purging pressure between the main injection ports. Therefore, a purging pressure test device is needed to measure the purging pressure of each main injection port, and then evaluate the purging design structure of the main injection port and test the purging effect.

[0032] Referring to Figures 1 to 3 The nozzle purging pressure measuring device includes a test cylinder 101 and a nozzle test piece 107. The test section cylinder 101 provides an air flow chamber 11, and the nozzle test piece 107 is arranged at the end of the test section cylinder 101 and communicates with the air flow chamber 11.

[0033] Further, a first mounting flange 103 is fixed on the test section cylinder 101, and a second mounting flange 104 is fixed on the first mounting flange 103. The test section cylinder 101 is fixed with the nozzle test piece 107 through the first mounting flange 103 and the second mounting flange 104. A receiving portion mounting seat 102 is also provided on the outer wall surface of the test section cylinder 101.

[0034] As shown in Figures 4 to 11 The nozzle test piece 107 includes a vortex finder 108, a housing 109, an oil collecting ring 110, and an end cover 111. The vortex finder 108 is connected with the second mounting flange 104.

[0035] The end of the end cover 111 opposite to the gas flow direction, i.e. Figures 7-10 The end of the housing 109 opposite to the gas flow direction includes a housing connecting flange edge 113, and the end of the end cover connecting flange edge 115, the housing connecting flange edge 113 and the vortex finder 108 are fixed by a connecting piece 116. In some embodiments, a gasket 114 is also provided between the end cover connecting flange edge 115 and the housing connecting flange edge 113. The end cover connecting flange edge 115, the gasket 114 and the housing connecting flange edge 113 are sequentially fixed to the vortex finder 108 by using the connecting piece 116 such as a screw.

[0036] The housing 109 is located inside the vortex finder 108 and surrounds the vortex finder to form an annular gap 12. The housing 109 is provided with a first hole portion 122 which communicates with the annular gap 12. The first hole portion 122 is used for blowing the purging gas out of the nozzle test piece.

[0037] The vortex finder 108 is also provided with a fourth hole portion 18 which communicates with the annular gap 12.

[0038] The end cover 111 is located inside the shell 109, comprising an inner peripheral chamber 13 and a second hole part 117, which communicates with the inner peripheral chamber 13 and serves as a purge gas inlet. In some embodiments, the second hole part 117 is circumferentially arranged at a position close to the inner ring of the oil collecting ring 110 on the end cover 111.

[0039] The end of the end cover 111 along the gas flow direction comprises a radially contracted shaft shoulder 14, and the oil collecting ring 110 is provided with a groove 15 for accommodating the shaft shoulder 14. A second sealing ring 120 is arranged between the axial end of the shaft shoulder 14 of the end cover 111 and the end of the groove 15 of the oil collecting ring 110 for sealing, as shown in Figure 8 and Figure 9 so that the shaft shoulder 14 and the groove 15 are in axial sealing cooperation. However, there is an annular gap 17 between the axial end of the oil collecting ring 110 and the axial end of the end cover 111, which communicates with the first hole part 122 and the second hole part 117.

[0040] The oil collecting ring 110 is located at the end of the end cover 111 along the gas flow direction, i.e. the right side as shown in Figures 7 to 10 and is located inside the shell 109. The oil collecting ring 110 is clamped on the shell 109 by the outer shell clamping part 121 and is sealed by the first sealing ring 119, as shown in Figure 8 .

[0041] The oil collecting ring 110 comprises a pressure collection hole 125, a third hole part 124 and a fourth hole part 118, the fourth hole part 118 communicates with the second hole part 117 and the first hole part 122, and the third hole part 124 communicates with the pressure collection hole 125 and the first hole part 122. The gas in the third hole part 124 comes from the first hole part 122, and the air in the third hole part 124 and the pressure collection hole 125 is not flowing, and the pressure collection hole 125 is used to collect the pressure of the third hole part 124. The fourth hole part 118 is circumferentially staggered with the third hole part 124 and is used for the flow of purge gas. The axis of the pressure collection hole 125 is parallel to the axis of the test section cylinder 101, and the pressure data of the third hole part 124 obtained by the pressure collection hole 125 are collected in real time by using a pressure collection device.

[0042] Part of the inner wall of the oil collecting ring 110 surrounds the groove 15 for accommodating the shaft shoulder 14, and the fourth hole part 118 is arranged on the part of the inner wall.

[0043] The first sealing ring 119 is circumferentially arranged between the oil collecting ring 110 and the shell 109 for sealing. The outer wall of the oil collecting ring 110 is further provided with a boss 123 which abuts against the shell 109, as shown in Figure 10As shown, the bosses 123 are evenly distributed along the outer wall of the oil collecting ring 110, and the third hole part 124 is arranged on the boss 123. The boss 123 is used to extend the third hole part 124 to the inner wall of the shell 109, so as to ensure the position of the static pressure measurement.

[0044] Figure 7 Two air flow paths are shown. The first air flow path a flows from the air flow chamber 11 of the test section cylinder 101, passes through the fifth hole part 18 on the vortex generator 108, and then leaves the nozzle test piece 107 through the annular gap 12. The second air flow path b flows from the air flow chamber 11 of the test section cylinder 101, and then is divided into two air flows: b' flows through the second hole part 117 into the fourth hole part 118 on the oil collecting ring 110, and then flows into the annular gap 12 through the first hole part 122 on the shell 109, and then leaves the nozzle test piece 107; b" flows through the second hole part 117 into the annular gap 17 between the oil collecting ring 110 and the end cover 111, and then flows into the annular gap 12 from the first hole part 122 on the shell 109, and then leaves the nozzle test piece 107.

[0045] The pressure collecting device can collect the pressure value of the main nozzle 124 in real time after the test starts by connecting the pressure collecting hole 125.

[0046] The above measuring device designs a fuel nozzle test piece with a main nozzle (third hole part) and a purge gas structure. The main nozzle (third hole part), the purge gas inlet and outlet (second hole part), and the vortex generator of the corresponding flow channel of the fuel nozzle test piece can simulate the air flow conditions inside and outside the real nozzle. Furthermore, a test section cylinder for installing the nozzle test piece is designed. The test section cylinder can provide a certain air pressure, and the fuel nozzle test piece is installed downstream of the test section cylinder. Through the structural design, the static pressure tube is connected with the main nozzle to measure and collect the purge pressure of the main nozzle. Generally, a pressure scanning valve is used to measure and collect the purge pressure of multiple main nozzles. When the flow provided by the test section passes through the fuel nozzle purge structure, the purge positive pressure and the purge negative pressure will be generated at the main nozzle. The data of the purge positive / negative pressure will be collected by the static pressure tube

[0047] By measuring the purge pressure of the third hole part of the nozzle, the measuring device can test and verify the purge capacity of the fuel nozzle. Furthermore, the calculation results of CFD can be calibrated according to the observation results, the design optimization of the purge structure can be supported, and the fuel nozzle meeting the purge requirements can be obtained.

[0048] It should be noted that the above content uses the words "first", "second", and the like to limit the parts, which is only for the convenience of distinguishing the corresponding parts. If there is no further declaration, the above words have no special meaning, and therefore cannot be understood as a limitation on the protection scope of the present application.

[0049] In the description of the present application, it should be understood that the orientation words such as "front, back, up, down, left, right", "transverse, vertical, perpendicular, horizontal" and "top, bottom" and the like indicated orientation or position relationship is generally based on the orientation or position relationship shown in the drawings, only for the convenience of describing the present application and simplifying the description, without making the opposite statement, these orientation words do not indicate and imply that the device or element referred to must have a particular orientation or be constructed and operated in a particular orientation, therefore, it cannot be understood as a limitation on the scope of protection of the present application; the orientation words "inner, outer" refer to the inner and outer relative to the contour of each component.

[0050] At the same time, specific words are used in the present application to describe the embodiments of the present application. As "one embodiment", "an embodiment" and / or "some embodiments" means a certain feature, structure or characteristic related to at least one embodiment of the present application. Therefore, it should be emphasized and noted that the "an embodiment" or "one embodiment" or "an alternative embodiment" mentioned in different positions in the specification does not necessarily refer to the same embodiment. In addition, some features, structures or characteristics in one or more embodiments of the present application can be properly combined.

[0051] The utility model discloses although the above-mentioned with preferable embodiment, but it is not used to limit the utility model, any person skilled in the art can make possible change and modification without departing from the spirit and scope of the utility model. Therefore, all the contents without departing from the technical scheme of the utility model, according to the technical essence of the utility model, any modification, equivalent change and modification of the above embodiment, all fall into the protection scope defined by the utility model claims.

Claims

1. A nozzle blow pressure measuring device characterized by, The device comprises: a test section cylinder comprising an air flow chamber; a nozzle test piece arranged downstream of the test section cylinder and in communication with the air flow chamber, comprising: a vortex finder; a housing located inside the vortex finder and surrounding the vortex finder with an annular gap, comprising a first hole portion in communication with the annular gap; an end cover located inside the housing, comprising an inner peripheral chamber and a second hole portion in communication with the inner peripheral chamber; and an oil collecting ring located at an end of the end cover along the air flow direction and inside the housing, comprising a pressure collection hole, a third hole portion and a fourth hole portion, the fourth hole portion being in communication with the second hole portion and the first hole portion, the third hole portion being in communication with the pressure collection hole and the first hole portion, and the pressure collection hole being used for collecting the pressure of the third hole portion.

2. The measuring device of claim 1, wherein, A boss is arranged on the oil collecting ring and abuts against the housing, and the third hole portion is arranged on the boss.

3. The measuring device of claim 1, wherein, An axis of the pressure collection hole is parallel to an axis of the test section cylinder.

4. The measuring device of claim 1, wherein, The fourth hole portion is arranged in a circumferential staggered manner with the third hole portion.

5. The measuring device of claim 1, wherein, The oil collecting ring comprises a shell bayonet which abuts against an inner wall of the shell, and a first sealing ring is arranged in a circumferential distribution between the oil collecting ring and the housing.

6. The measuring device of claim 1, wherein, An annular gap is arranged between an axial end portion of the end cover and an axial end portion of the oil collecting ring, and the annular gap is in communication with the first hole portion and the second hole portion.

7. The measuring device of claim 6, wherein, An end portion of the end cover along the air flow direction comprises a radially contracted shaft shoulder, the oil collecting ring is provided with a groove accommodating the shaft shoulder, and the shaft shoulder and the groove are in sealing cooperation in the axial direction.

8. The measuring device of claim 1, wherein, End portions of the end cover on opposite sides along the air flow direction comprise an end cover connecting flange edge, end portions of the housing on opposite sides along the air flow direction comprise a housing connecting flange edge, and the end cover connecting flange edge, the housing connecting flange edge and an end portion of the vortex finder are fixed by a connecting piece.

9. The measuring device of claim 1, wherein, The device further comprises a pressure collection device in communication with the pressure collection hole.

10. The measuring device of claim 1, wherein, The vortex finder is provided with a fifth hole portion in communication with the annular gap.

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