Filler device for liquid rocket engine thrust chamber barrel cooling channel testing

Abstract

A filling device for testing cooling channels in the thrust chamber of a liquid rocket engine is disclosed. This device can be used for flow resistance testing of a single-hole rectangular cooling channel in the thrust chamber of a liquid rocket engine. It includes a filling section, a sealing section, a main sealing gasket, a sealing ring, a connecting plate, a cylinder, and a liquid inlet pipe. The sealing ring is installed in a groove at the bottom of the sealing section. The filling section and the sealing section are fixedly connected. The connecting plate is connected to the cylinder. The filling section has a quick-positioning hook and is connected to the connecting plate. A groove is provided at the top of the sealing section, and the main sealing gasket is located within the groove. The center of the main sealing gasket is rectangularly hollowed out, and a miniature filling tube extending from the bottom of the groove of the sealing section extends through the main sealing gasket. A liquid inlet hole is provided on the side of the filling section, and the liquid inlet pipe is connected to the liquid inlet hole on the side of the filling section. Both the filling section and the sealing section have internal flow channels to connect the liquid inlet hole to the miniature filling tube. This invention can determine the flow coefficient and flow characteristics of each cooling channel.

Description

Technical Field

[0001] This invention relates to a filling device for testing the cooling channel of the thrust chamber of a liquid rocket engine, which can be used for testing the flow resistance of a single-hole rectangular cooling channel in the thrust chamber of a liquid rocket engine. Background Technology

[0002] The thrust chamber is a core component of a liquid rocket engine, and the flow uniformity and flow resistance characteristics of its cooling channels directly affect the heat transfer efficiency and combustion stability of the rocket engine. Differences in the processing conditions of each cooling channel will affect the flow rate of cooling hydrogen within the channel. When the local flow resistance is too high or the flow coefficient is too low, the cooling hydrogen flow rate allocated to the cooling channel will be less than the design value. In severe cases, it can cause the inner wall to burn through and the thrust chamber to burn out.

[0003] Traditional fluid flow testing devices are only used for overall fluid flow testing of the thrust chamber of liquid rocket engines, and cannot achieve fluid inlet and sealing of a single rectangular cooling channel. Therefore, it is necessary to design a fluid flow testing and filling device for a single cooling channel of the thrust chamber, which can determine the flow coefficient and flow characteristics of a single channel of the thrust chamber. Currently, there is no such testing device that can meet the requirements of fluid inlet and sealing of a single cooling channel. Summary of the Invention

[0004] The technical problem to be solved by the present invention is to overcome the shortcomings of the prior art, so as to achieve the filling and sealing of a single cooling channel in the thrust chamber body by applying preload through the cylinder, and to measure the flow coefficient and flow characteristics of each cooling channel.

[0005] The objective of this invention is achieved through the following technical solutions:

[0006] A refueling device for testing the cooling channel of the thrust chamber of a liquid rocket engine includes a refueling section, a sealing section, a main sealing gasket, a sealing ring, a transition plate, a cylinder, and a liquid inlet pipe.

[0007] A sealing ring is installed in the groove at the bottom of the sealing section; the filling section and the sealing section are fixedly connected; the adapter plate is connected to the cylinder, the filling section is equipped with a quick-positioning hook, and the filling section is connected to the adapter plate;

[0008] The top of the sealing section has a groove, and the main sealing gasket is located in the groove; the center part of the main sealing gasket is a rectangular hollow, and the micro filling tube extending from the bottom of the groove of the sealing section extends out through the main sealing gasket;

[0009] The filling section has a liquid inlet hole on its side, and the liquid inlet pipe is connected to the liquid inlet hole on the side of the filling section. Both the filling section and the sealing section have internal flow channels to connect the liquid inlet hole to the micro filling tube core.

[0010] In one embodiment of the present invention, the filling device further includes a first fastener, which fixes the filling section and the sealing section together.

[0011] In one embodiment of the present invention, the filling device further includes a second fastener, and the filling section is connected to the adapter plate through the second fastener.

[0012] In one embodiment of the present invention, an O-ring groove is provided at the bottom of the sealing section, and the sealing ring is located in the O-ring groove.

[0013] In one embodiment of the present invention, the cylinder is provided with a control air inlet and an exhaust port, and a deceleration nozzle is provided in front of the control air inlet to slow down the running speed of the cylinder.

[0014] In one embodiment of the present invention, a gas distribution platform is used to supply control gas to the cylinder, and the cylinder is opened by an electric current signal. The cylinder generates a preload force, which drives the filling device to move forward horizontally.

[0015] In one embodiment of the present invention, the main sealing gasket is used to seal the filling device and the cooling channel of the test piece.

[0016] In one embodiment of the present invention, the assembly and operation process of the dispensing device is as follows:

[0017] a. Place the sealing ring in the groove of the sealing section;

[0018] b. Connect the filling section and the sealing section;

[0019] c. Connect the adapter plate to the cylinder;

[0020] d. Quickly connect the filling section to the adapter plate using the positioning hook;

[0021] e. After placing the main sealing gasket through the miniature filling tube into the groove at the top of the sealing section and completing the alignment of the rectangular cooling channel of the thrust chamber body, the gas distribution platform supplies control gas to the cylinder. The cylinder is opened by the current signal. The pre-tightening force generated by the cylinder drives the entire filling device to move forward horizontally. The miniature filling tube is inserted into the cooling channel opening of the thrust chamber body. The main sealing gasket is evenly compressed on the circumferential arc surface of the cooling channel of the test piece, producing a sealing effect.

[0022] f. Allow water to flow in through the side inlet of the filling section and enter the cooling channel of the thrust chamber body through the micro filling tube core;

[0023] g. After filling, cut off the supply of test medium, open the vent hole of the cylinder, the cylinder completes the retraction, and the filling device is removed from the cooling channel hole of the thrust chamber body;

[0024] h. Repeat the cylinder sealing action described above to complete the flow resistance test for different cooling channels. After the entire test is completed, remove the filling device to complete the entire test procedure.

[0025] Compared with the prior art, the present invention has the following advantages:

[0026] (1) The filling device of the present invention, combined with the automated device of visual recognition, realizes for the first time the liquid flow test of each cooling channel of the thrust chamber body, evaluates the flow characteristics of each cooling channel of the thrust chamber body, and improves the engine test coverage.

[0027] (2) The filling device of the present invention achieves the sealing of a single 2mm wide cooling channel in the thrust chamber body, providing the possibility for testing the cooling channel of the engine thrust chamber body.

[0028] (3) The filling device of the present invention adopts an insertion sealing design. The filling tube core with a width of 1mm is inserted into the cooling channel with a width of 2mm by applying pre-tightening force through the cylinder, and the main sealing gasket is used to achieve sealing. The insertion sealing design makes the flow resistance basically constant for each measurement, which improves the accuracy of the test.

[0029] (4) The bottom of the square groove of the filling device of the present invention is designed with an arc, and the arc is consistent with the test piece. During the process of the cylinder applying the pre-tightening force, it is transmitted circumferentially to the main sealing gasket, resulting in a better sealing effect.

[0030] (5) The filling device of the present invention adopts a segmented design, which is convenient for installation and disassembly. It also has a main sealing gasket that can be removed and replaced. The structure is simple and easy to operate. Similar structures and seals can all adopt this form, which is highly practical. Attached Figure Description

[0031] Figure 1 This is a schematic diagram of the overall filling device.

[0032] Figure 2 This is a horizontal cross-sectional view of the filling device.

[0033] Figure 3 This is a vertical cross-sectional view of the sealing section.

[0034] Figure 4 This is a schematic diagram of the sealing section.

[0035] Reference numerals: Filling section-1, Sealing section-2, Main sealing gasket-3, Sealing ring-4, First fastener-5, Second fastener-6, Adapter plate-7, Cylinder-8, Liquid inlet pipe-9, Thrust chamber body cooling channel opening-10. Detailed Implementation

[0036] To make the objectives, technical solutions, and advantages of the present invention clearer, the embodiments of the present invention will be described in further detail below with reference to the accompanying drawings.

[0037] A refueling device for testing the cooling channel of the thrust chamber of a liquid rocket engine is shown in the schematic diagram below. Figure 1 As shown, it has the functions of media filling and sealing. A horizontal cross-sectional view of the filling device is shown below. Figure 2 As shown, the vertical cross-sectional view of the sealing section is as follows: Figure 3 The diagram shows the schematic relationship between the main sealing gasket and the sealing section; the sealing section sealing diagram is shown below. Figure 4 The diagram illustrates the relationship between the sealing section and the product cooling channel.

[0038] A filling device for testing the cooling channel of the thrust chamber of a liquid rocket engine includes a filling section 1, a sealing section 2, a main sealing gasket 3, a sealing ring 4, a first fastener 5, a second fastener 6, an adapter plate 7, a cylinder 8, and a liquid inlet pipe 9.

[0039] The filling section 1 and the sealing section 2 have the same set of bolt holes. The bottom of the sealing section 2 has an O-ring groove. The sealing ring 4 is placed in the O-ring groove, and the filling section 1 and the sealing section 2 are fixedly connected by the first fastener 5. The adapter plate 7 has bolt holes and is connected to the cylinder 8 by countersunk bolts. The filling section 1 is equipped with a quick-positioning claw, which is connected to the adapter plate 7 by the second fastener 6.

[0040] The sealing section 2 has a groove at its top, into which the main sealing gasket 3 is placed. The center of the main sealing gasket 3 is rectangularly hollowed out. A miniature filling tube extending from the bottom of the groove at the top of the sealing section 2 passes through the main sealing gasket 3 and extends out.

[0041] The filling section 1 is provided with a liquid inlet hole on its side, and the liquid inlet pipe 9 is connected to the liquid inlet hole on the side of the filling section 1 by a screw connection. Both the filling section 1 and the sealing section 2 are provided with internal flow channels.

[0042] The cylinder 8 is equipped with a control air inlet and an exhaust port. A deceleration nozzle is provided in front of the control air inlet to slow down the cylinder's running speed.

[0043] The assembly and operation process of the filling device of the present invention is as follows:

[0044] a. Place the sealing ring 4 in the O-ring groove of the sealing section 2.

[0045] b. Connect the filling section 1 and the sealing section 2 using the first fastener 1.

[0046] c. Connect the adapter plate 7 to the cylinder 8 using countersunk bolts.

[0047] d. Quickly connect the filling section 1 to the adapter plate 7 using the positioning hook.

[0048] e. Place the main sealing gasket 3 through the miniature filling tube into the square groove of the sealing section 2. After aligning the rectangular cooling channel of the thrust chamber body, the gas distribution platform supplies 0.5 MPa of control gas to the cylinder 8. The cylinder is opened by the current signal, and the cylinder generates a preload force of about 360 N. The cylinder pushes the filling device forward horizontally, and the miniature filling tube is inserted into the cooling channel opening 10 of the thrust chamber body. The main sealing gasket 3 is uniformly compressed on the circumferential arc surface of the cooling channel of the test piece, producing a sealing effect.

[0049] f. Water flows in through the side inlet hole of the filling section 1 and enters the cooling channel of the thrust chamber body through the micro filling tube.

[0050] g. After filling, cut off the supply of test medium, open the vent hole of cylinder 8, the cylinder completes the retraction, and the filling device is withdrawn from the cooling channel hole of the thrust chamber body.

[0051] h. Repeat the sealing action of cylinder 8 as described above to complete the flow resistance test for different cooling channels. After the entire test is completed, remove the filling device to complete the entire test procedure.

[0052] The contents not described in detail in this specification are common knowledge to those skilled in the art.

[0053] Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solutions of the present invention by utilizing the methods and techniques disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and alterations made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the protection scope of the technical solutions of the present invention.

Claims

1. A refueling device for testing the cooling channel of the thrust chamber of a liquid rocket engine, characterized in that, It includes the filling section (1), sealing section (2), main sealing gasket (3), sealing ring (4), adapter plate (7), cylinder (8), and liquid inlet pipeline (9); A sealing ring (4) is installed in the groove at the bottom of the sealing section (2); the filling section (1) and the sealing section (2) are fixedly connected; the adapter plate (7) is connected to the cylinder (8), the filling section (1) is provided with a quick positioning hook, and the filling section (1) is connected to the adapter plate (7); The top of the sealing section (2) is provided with a groove, and the main sealing gasket (3) is located in the groove; the center part of the main sealing gasket (3) is a rectangular hollow, and the micro filling tube core extending from the bottom of the groove of the sealing section (2) extends out through the main sealing gasket (3); The filling section (1) is provided with an inlet hole on the side, and the inlet pipe (9) is connected to the inlet hole on the side of the filling section (1). Both the filling section (1) and the sealing section (2) are provided with internal flow channels to connect the inlet hole to the micro filling tube core.

2. The dispensing device according to claim 1, characterized in that, The filling device also includes a first fastener (5) for fixing the filling section (1) and the sealing section (2) together.

3. The dispensing device according to claim 1, characterized in that, The filling device also includes a second fastener (6), and the filling section (1) is connected to the adapter plate (7) via the second fastener (6).

4. The dispensing device according to claim 1, characterized in that, The bottom of the sealing section (2) is provided with an O-ring groove, and the sealing ring (4) is located in the O-ring groove.

5. The dispensing device according to claim 1, characterized in that, The cylinder (8) is equipped with a control air inlet and an exhaust port. A deceleration nozzle is provided in front of the control air inlet to slow down the running speed of the cylinder (8).

6. The dispensing device according to claim 1, characterized in that, The control gas is supplied to the cylinder (8) by the gas distribution platform. The cylinder (8) is opened by the current signal. The cylinder (8) generates a pre-tightening force, which drives the filling device to move forward horizontally.

7. The dispensing device according to claim 1, characterized in that, The main sealing gasket (3) is used to seal the filling device and the cooling channel of the test piece.

8. The dispensing device according to claim 1, characterized in that, The assembly and operation process of the refueling device is as follows: a. Place the sealing ring (4) in the groove of the sealing section (2); b. Connect the filling section (1) and the sealing section (2); c. Connect the adapter plate (7) to the cylinder (8); d. Quickly connect the filling section (1) to the adapter plate (7) using the positioning hook; e. Place the main sealing gasket (3) through the micro filling tube core into the groove at the top of the sealing section (2). After completing the alignment of the rectangular cooling channel of the thrust chamber body, the gas distribution platform provides control gas to the cylinder (8). The cylinder (8) is opened by the current signal. The pre-tightening force generated by the cylinder (8) drives the entire filling device to move forward horizontally. The micro filling tube core is inserted into the cooling channel opening (10) of the thrust chamber body. The main sealing gasket (3) is uniformly compressed on the circumferential arc surface of the cooling channel of the test piece, producing a sealing effect. f. Water flows in through the side inlet hole of the filling section (1) and enters the cooling channel of the thrust chamber body through the micro filling tube core; g. After the filling is completed, the supply of test medium is cut off, the vent of cylinder (8) is opened, cylinder (8) is retracted, and the filling device is withdrawn from the cooling channel hole of the thrust chamber body; h. Repeat the sealing action of cylinder (8) above to complete the flow resistance test of different cooling channels.

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