Aviation kerosene testing device

Abstract

The utility model relates to an aviation kerosene testing device in the technical field of aviation kerosene detection, which comprises a testing tank, a detection shell communicated with an inner cavity of the testing tank is arranged on the upper section of the outer side of the testing tank, a combustible gas alarm is arranged in the detection shell, and a first driving motor is arranged in the middle of the top surface of the testing tank. An output shaft of the first driving motor faces upwards and is coaxially sleeved with a follow-up sleeve, and a sleeve body of the follow-up sleeve is provided with a wavy sliding way in the circumferential direction of the follow-up sleeve. According to the aviation kerosene heating device, the follow-up sleeve is driven to rotate through the first driving motor, in the rotating process of the follow-up sleeve, the position, corresponding to the sliding piece, of the sliding way gradually descends or ascends, the function of driving the sliding piece and the rotating rod to reciprocate up and down is achieved, and therefore aviation kerosene is evenly heated. The first driving motor only needs to rotate in a specific direction to drive the rotating rod to move up and down in a reciprocating mode, and the technical problem that forward rotation and reverse rotation of the motor are frequently switched is solved.

Description

Technical Field

[0001] The utility model relates to the technical field of aviation kerosene detection, in particular to an aviation kerosene testing device. Background Art

[0002] Aviation kerosene is one of petroleum products, also known as odorless aviation kerosene. It is mainly composed of hydrocarbon compounds with different fractions. Aviation kerosene has a suitable density, high calorific value, good combustion performance, can burn rapidly, stably, continuously and completely, and has a small combustion area, less carbon deposition and is not easy to coke; it has good low-temperature fluidity and can meet the requirements of oil product fluidity in cold and low-temperature regions and high-altitude flights; it has high cleanliness, no mechanical impurities and harmful substances such as moisture, and low sulfur content, especially mercaptan sulfur content, and has little corrosion to machine parts.

[0003] In order to better store aviation kerosene, it is necessary to detect the volatility of aviation kerosene. The existing Chinese patent (Publication No.: CN217212714U) discloses an aviation kerosene simulation testing device, which discloses a testing shell. A gear is rotatably installed in the middle of the upper end face of the testing shell. A first motor is connected to the gear. The left and right sides of the upper end face of the testing shell are both slidably penetrated with sliding sleeves. A rotating rod is rotatably penetrated through the sliding sleeve. A plurality of stirring blades are fixedly connected to the outer surface of the middle and lower parts of the rotating rod. The frequent forward and reverse rotation of the first motor of this device drives the frequent forward and reverse rotation of the gear, and then drives the rotating rods on both sides of the gear to move up and down reciprocally. However, the frequent forward and reverse rotation of the motor easily causes the motor to be damaged.

[0004] Therefore, we designed an aviation kerosene testing device. Content of the Utility Model

[0005] In order to overcome the deficiencies in the background art, the utility model discloses an aviation kerosene testing device.

[0006] To achieve the above invention purpose, the utility model adopts the following technical solutions:

[0007] An aviation kerosene testing device includes a testing tank. An inspection shell communicating with its inner cavity is arranged on the upper outer section of the testing tank, and a combustible gas alarm is installed in the inspection shell. A first driving motor is arranged in the middle of the top surface of the testing tank. The output shaft of the first driving motor faces upward, and a follower sleeve is coaxially sleeved thereon. And a wavy slideway is arranged along the circumferential direction of the follower sleeve body;

[0008] A plurality of rotatable rotating rods are slidably penetrated up and down through the top surface of the testing tank corresponding to the position outside the follower sleeve, and a sliding member cooperating with the slideway is rotatably sleeved on the upper section of the rotating rod, so as to follow the rotation of the follower sleeve to move up and down reciprocally, and then drive the corresponding rotating rod to move up and down reciprocally; a stirring fan blade for stirring the aviation kerosene to be tested is arranged on the lower section of the rotating rod;

[0009] A second driving motor for driving the rotation is provided at the top of the rotating rod.

[0010] Preferably, a driving gear is fixedly sleeved on the outer end of the output shaft of the first driving motor. A plurality of transmission gears are meshed on the circumferential side of the driving gear. The wheel shaft of the transmission gear is rotatably connected to the top of the test tank. An internal gear ring is meshed on the outside of the transmission gear, and the internal gear ring is coaxially fixed to the follower sleeve.

[0011] Preferably, a convex ring rotatably connected to the follower sleeve is provided on the top surface of the test tank.

[0012] Preferably, an installation frame is provided at the top of the test tank, and a sliding frame that is slidably connected up and down to the installation frame is provided at the fixing part of the second driving motor.

[0013] Preferably, the test tank is provided with a temperature detection device for detecting the temperature of the aviation kerosene in its inner cavity.

[0014] Preferably, a display screen is inlaid on the detection housing.

[0015] Preferably, a spiral heating pipe is provided on the body of the test tank.

[0016] Preferably, a liquid inlet pipe with a sealing structure is provided on one side of the test tank.

[0017] Preferably, an aggregation structure is provided at the bottom of the inner cavity of the test tank, and a liquid discharge pipe with a valve is provided at the bottom of the aggregation structure.

[0018] Due to the adoption of the above-mentioned technical solution, the utility model has the following beneficial effects:

[0019] 1. The first driving motor can drive the follower sleeve to rotate. During the rotation of the follower sleeve, the nearest position of the slideway corresponding to the sliding part gradually descends or ascends, and after gradually descending or ascending, it begins to gradually ascend or descend, realizing the function of driving the sliding part and the rotating rod to move up and down reciprocally, so that the aviation kerosene is evenly heated. Compared with the prior art, the first driving motor only needs to rotate in a specific direction to complete the function of driving the rotating rod to move up and down reciprocally, solving the technical problem of frequent forward and reverse switching of the motor.

[0020] 2. The arrangement of the driving gear, the transmission gear and the internal gear ring can effectively reduce the rotation speed of the follower sleeve, and further can effectively reduce the up and down movement of the rotating rod, preventing the aviation kerosene from splashing due to the too fast speed of the up and down reciprocating movement of the rotating rod and affecting the detection result. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 is a schematic structural diagram of the utility model;

[0022] Figure 2 This is a cross-sectional view of the present utility model;

[0023] Figure 3 This is a schematic structural view of the part that drives the rotating rod in the present utility model.

[0024] In the figure: 1, test tank; 101, mounting rack; 102, spiral heating tube; 103, liquid inlet pipe; 104, liquid discharge pipe; 2, detection housing; 201, display screen; 3, combustible gas alarm; 4, first driving motor; 401, driving gear; 402, transmission gear; 403, internal gear ring; 5, follower sleeve; 501, slideway; 6, rotating rod; 601, stirring fan blade; 7, sliding member; 8, second driving motor; 801, sliding rack; 9, convex ring. Specific embodiments

[0025] The present utility model can be explained in detail through the following embodiments. The purpose of disclosing the present utility model is to protect all technical improvements within the scope of the present utility model. In the description of the present utility model, it should be understood that if there are terms such as "upper", "lower", "front", "rear", "left", "right", etc. indicating the orientation or positional relationship, it is only corresponding to the drawings of the present application for the convenience of describing the present utility model; it should be understood that if there are terms such as "end", "side", "end part", "side part", "lateral", "longitudinal", etc. indicating the orientation or positional relationship, it is only corresponding to the length and width of the corresponding component, that is, the "end part" indicates the head and tail regions in the length direction of the corresponding component, and the "side part" indicates the head and tail regions in the width direction of the corresponding component; it is for the convenience of describing the present utility model rather than indicating or implying that the device or element referred to must have a specific orientation.

[0026] Embodiment 1, in combination with the attached Figures 1 - 3 , an aviation kerosene testing device, including a test tank 1. As needed, a liquid inlet pipe 103 with a sealing structure is provided on one side of the test tank 1, that is, the aviation kerosene to be tested can be poured into the inner cavity of the test tank 1 through the liquid inlet pipe 103; as needed, the sealing structure can be a sealing cover or a sealing plug, which is specifically designed according to actual needs and is not specifically limited here. As needed, the bottom of the inner cavity of the test tank 1 has an aggregation structure, and a liquid discharge pipe 104 with a valve is provided at the bottom of the aggregation structure; as needed, the aggregation structure can be a resulting conical cavity, a lower hemispherical cavity, or other structures that can aggregate a small amount of kerosene at the liquid discharge pipe 104 so that all the aviation kerosene can be discharged through the liquid discharge pipe 104. As needed, a spiral heating tube 102 is provided on the tank body of the test tank 1, that is, the aviation kerosene in the inner cavity of the test tank 1 can be heated through the spiral heating tube 102, and then the aviation kerosene at different temperatures can be tested; as needed, the spiral heating tube 102 can be a steam pipe, a heat oil pipe, or a resistance heating tube; during use, the spiral heating tube 102 is connected to its supporting external heating equipment.

[0027] Furthermore, the test tank 1 is provided with a temperature detection device for detecting the temperature of kerosene in its inner cavity; if necessary, the temperature detection device can be a temperature sensor.

[0028] On the upper section outside the test tank 1, a detection housing 2 communicating with its inner cavity is provided, and a combustible gas alarm 3 is installed inside the detection housing 2; if necessary, a display screen 201 is inlaid on the detection housing 2. Furthermore, the display screen 201 is connected to the temperature sensor to facilitate displaying the temperature value detected by the temperature sensor.

[0029] In the middle of the top surface of the test tank 1, a first driving motor 4 is provided. The output shaft of the first driving motor 4 faces upward, and a follower sleeve 5 is coaxially sleeved thereon. Moreover, a wavy slideway 501 is provided along the circumferential direction of the body of the follower sleeve 5; that is, the rotation of the output shaft of the first driving motor 4 can drive the rotation of the follower sleeve 5.

[0030] A plurality of rotatable rotating rods 6 are slidably penetrated up and down through the top surface of the test tank 1 corresponding to the position outside the follower sleeve 5. A sliding member 7 cooperating with the slideway 501 is rotatably sleeved on the upper section of the rod body of the rotating rod 6 to facilitate reciprocating up and down movement following the rotation of the follower sleeve 5, thereby driving the corresponding rotating rod 6 to reciprocate up and down; if necessary, one side of the sliding member 7 corresponding to the follower sleeve 5 has a mating portion inserted into the slideway 501; if necessary, the cross-section of the slideway 501 can be semicircular, and the mating portion is spherical or hemispherical to facilitate the relative movement of the mating portion in the slideway 501 smoothly. That is, during the rotation of the follower sleeve 5, the nearest position of the slideway 501 corresponding to the sliding member 7 gradually descends or ascends, and after gradually descending or ascending, it begins to gradually ascend or descend, realizing the function of driving the sliding member 7 to reciprocate up and down.

[0031] A stirring fan blade 601 for stirring the aviation kerosene to be tested is provided at the lower section of the rotating rod 6; a second driving motor 8 for driving its rotation is provided at the top of the rotating rod 6; specifically, the second driving motor 8 can move up and down relative to the test tank 1.

[0032] If necessary, a mounting frame 101 is provided at the top of the test tank 1, and a sliding frame 801 slidably connected up and down to the mounting frame 101 is provided at the fixing part of the second driving motor 8; that is, the up and down movement of the rotating rod 6 can drive the second driving motor 8 and the sliding frame 801 to move up and down, so that the rotating rod 6 and the second driving motor 8 are relatively stationary in the height direction, ensuring that the output shaft of the second driving motor 8 can be stably connected to the rotating rod 6.

[0033] During use, jet fuel is put into the test tank 1 through the liquid inlet pipe 103, and then the jet fuel is heated at different temperatures by the spiral heating pipe 102. When the combustible gas alarm 3 detects the volatile gaseous jet fuel, the heating is stopped, and then the volatility of the jet fuel at a specific temperature is measured. During heating, the first drive motor 4 and the second drive motor 8 are started, and the second drive motor 8 drives the rotating rod 6 to rotate. The first drive motor 4 drives the follower sleeve 5 to rotate. During the rotation of the follower sleeve 5, the nearest position of the slideway 501 corresponding to the sliding member 7 gradually descends or ascends, and after gradually descending or ascending, it begins to gradually ascend or descend, realizing the function of driving the sliding member 7 to move up and down reciprocally, so as to make the jet fuel evenly heated.

[0034] In the embodiment, the number of the rotating rods 6 is four, and the four rotating rods 6 are arranged at equal angles around the central axis of the test tank 1. The slideway 501 sleeved on the follower sleeve 5 has two wave crests and two wave troughs. At this time, the heights of the two diagonal rotating rods 6 are the same, and the motion postures of the two adjacent rotating rods 6 are opposite, that is, when one rotating rod 6 moves upward, the two adjacent rotating rods 6 move downward, so that the jet fuel can be better evenly heated.

[0035] In the embodiment, the number of the rotating rods 6 is two in symmetry. The slideway 501 sleeved on the follower sleeve 5 has one wave crest and one wave trough. At this time, the motion postures of the two rotating rods 6 are opposite, that is, when one rotating rod 6 moves upward, the other rotating rod 6 moves downward, so that the jet fuel can be better evenly heated.

[0036] Embodiment Two, in combination with the attached Figures 1 - 3 A jet fuel testing device. On the basis of Embodiment One, in order to reduce the reciprocating motion frequency of the rotating rod 6 and prevent the rotating rod 6 from driving the jet fuel to splash due to the too fast reciprocating motion speed, which affects the detection result. A driving gear 401 is fixedly sleeved on the outer end of the output shaft of the first drive motor 4. A plurality of transmission gears 402 are meshed on the circumferential side of the driving gear 401, and the wheel shafts of the transmission gears 402 are rotatably connected to the top of the test tank 1. An internal gear ring 403 is meshed on the outside of the transmission gear 402, and the internal gear ring 403 is coaxially fixed to the follower sleeve 5.

[0037] Furthermore, in order to ensure the stability of the follower sleeve 5, a convex ring 9 rotatably connected to the follower sleeve 5 is provided on the top surface of the test tank 1.

[0038] As required, the wheel shaft of the transmission gear 402 is rotatably connected to the top of the test tank 1 by being rotatably connected to the mounting frame 101. As required, the rotating rod 6 slides up and down through the mounting frame 101 to increase the stability of the rotating rod 6.

[0039] As required, the rotating rod 6 can be connected to the mounting frame 101 through a sliding bearing.

[0040] The rotation of the first driving motor 4 is set in this way to drive the driving gear 401 to rotate. The rotation of the driving gear 401 drives the transmission gear 402 to rotate, and then drives the internal gear ring 403 to rotate slowly. Since the internal gear ring 403 is fixedly connected to the follower sleeve 5, the follower sleeve 5 also rotates slowly, and thus the up-and-down movement of the rotating rod 6 can be effectively reduced.

[0041] The parts not detailed in the present utility model are the prior art. For those skilled in the art, it is obvious that the present utility model is not limited to the details of the above exemplary embodiments, and can be implemented in other specific forms without departing from the spirit or basic characteristics of the present utility model; therefore, from any point of view, the embodiments should be regarded as exemplary and non-limiting, aiming to include all changes falling within the meaning and scope of the equivalent elements in the present utility model.

Claims

1. An aviation kerosene testing device, comprising a testing tank (1), an upper section on the outer side of the testing tank (1) is provided with a detection housing (2) communicating with its inner cavity, and a combustible gas alarm (3) is installed in the detection housing (2), characterized in that: In the middle of the top surface of the test tank (1), there is a first driving motor (4). The output shaft of the first driving motor (4) faces upward, and a follower sleeve (5) is coaxially sleeved thereon. Along the circumferential direction of the body of the follower sleeve (5), there is a wavy slideway (501). A plurality of rotatable rotating rods (6) are slidably inserted up and down through the top surface of the test tank (1) at positions corresponding to the outer side of the follower sleeve (5). A sliding member (7) that cooperates with the slideway (501) is rotatably sleeved on the upper section of the rod body of the rotating rod (6), so as to reciprocate up and down following the rotation of the follower sleeve (5), and further drive the corresponding rotating rod (6) to reciprocate up and down. A stirring fan blade (601) for stirring the aviation kerosene to be tested is provided at the lower section of the rotating rod (6). A second driving motor (8) for driving the rotation of the rotating rod (6) is provided at the top of the rotating rod (6).

2. The aviation kerosene testing device according to claim 1, wherein: A driving gear (401) is fixedly sleeved on the outer end of the output shaft of the first driving motor (4). A plurality of transmission gears (402) are meshed on the circumferential side of the driving gear (401). The axle of the transmission gear (402) is rotatably connected to the top of the test tank (1). An internal gear ring (403) is meshed on the outer side of the transmission gear (402), and the internal gear ring (403) is coaxially fixed to the follower sleeve (5).

3. The aviation kerosene testing device according to claim 2, wherein: A convex ring (9) rotatably connected to the follower sleeve (5) is provided on the top surface of the test tank (1).

4. The aviation kerosene testing device according to claim 1, characterized in that: An installation frame (101) is provided at the top of the test tank (1). A sliding frame (801) that is slidably connected up and down to the installation frame (101) is provided at the fixed part of the second driving motor (8).

5. The aviation kerosene testing device according to claim 1, characterized in that: The test tank (1) is provided with a temperature detection device for detecting the temperature of the aviation kerosene in its inner cavity.

6. The aviation kerosene testing device according to claim 1, characterized in that: A display screen (201) is inlaid on the detection housing (2).

7. The aviation kerosene testing device according to claim 1, wherein: A spiral heating pipe (102) is provided on the body of the test tank (1).

8. An aviation kerosene testing device according to claim 1, characterized in that: A liquid inlet pipe (103) with a sealing structure is provided on one side of the test tank (1).

9. The aviation kerosene testing device according to claim 1, wherein: The bottom of the inner cavity of the test tank (1) has an aggregation structure, and a drain pipe (104) with a valve is provided at the bottom of the aggregation structure.

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