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Rocket turbopump floating ring seal testing testbed

A rocket turbine and sealing test technology, which is applied to rocket engine devices, pump control, non-variable pumps, etc., can solve the problems of flow-induced vibration instability, increased rotor vibration, low stability and reliability of rocket engines, etc.

Inactive Publication Date: 2020-09-08
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The present invention solves the phenomenon that the existing turbopump rotor is prone to flow-induced vibration instability during operation, resulting in increased rotor vibration. Under the oxygen-enriched condition of the turbopump, oxygen-enriched combustion is very easy to occur, and the rocket engine has stability and The problem of low reliability, and then provide a rocket turbo pump floating ring seal test bench

Method used

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  • Rocket turbopump floating ring seal testing testbed
  • Rocket turbopump floating ring seal testing testbed
  • Rocket turbopump floating ring seal testing testbed

Examples

Experimental program
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specific Embodiment approach 1

[0023] Specific implementation one: as Figures 1 to 4 As shown, the rocket turbo pump floating ring seal test bench of this embodiment includes a test base platform 1, a servo motor 2, a variable speed gearbox 3, a rotor 4, a test bench body, a T-slot guide 6, two bearing seats 5, Two positioning rings 13 and a plurality of eddy current displacement sensors 7; two T-slot guide rails 6 are arranged in sequence along the length direction of the test foundation platform 1, and the servo motor 2 and the variable speed gearbox 3 are arranged on the T-slot guide rail 6 in sequence, The rotor 4 is installed on the T-slot guide rail 6 through two bearing seats 5, and the output shaft of the servo motor 2 is connected with the rotor 4 through the transmission gearbox 3 and the coupling; the test bench body includes a front cavity 8 and a middle cavity 9. , the rear cavity 10 and two cavity labyrinth seals, both ends of the test bench body are provided with a positioning ring 13 and a ...

specific Embodiment approach 2

[0024] Specific implementation two: as figure 1 and image 3 As shown, in this embodiment, the front cavity 8 , the middle cavity 9 and the rear cavity 10 are fixedly connected together by a plurality of through bolts, and the two adjacent cavities are sealed by a sealing end face gasket.

[0025] In this way, the sealing between the two adjacent cavities is sealed by the sealing end face gasket, and the sealing between the front cavity 8, the middle cavity 9 and the rear cavity 10 is realized. At the same time, the front cavity 8 and the middle cavity 9 are sealed. The detachable connection with the rear cavity 10 realizes the installation and removal of the floating ring.

[0026] Other components and connection relationships are the same as in the first embodiment.

specific Embodiment approach 3

[0027] Specific implementation three: as figure 1 and figure 2 As shown, the T-slot guide 6 in this embodiment is composed of a first T-slot guide and a second T-slot guide. The first T-slot guide and the second T-slot guide are machined with a plurality of T-slots along their lengths. The groove, the servo motor 2 and the gear box 3 are installed on the upper end surface of the first T-slot guide rail, and the rotor 4, the test bench body and the two bearing seats 5 are installed on the upper end surface of the second T-slot guide rail.

[0028] This design facilitates adjusting the position of the servo motor 2 and the transmission gearbox 3 on the first T-slot guide rail, and facilitates adjusting the position of the rotor 4, the test bench body and the two bearing seats 5 on the second T-slot guide rail.

[0029] Other compositions and connection relationships are the same as in the first or second embodiment.

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Abstract

The invention discloses a testbed, in particular to a rocket turbopump floating ring seal testbed. The rocket turbopump floating ring seal testbed solves the problems that in the running process of anexisting turbopump rotor, the phenomenon of flow-induced vibration instability is likely to happen, rotor vibration is increased, oxygen-enriched combustion is extremely likely to happen under the oxygen-enriched condition of a turbopump, and a rocket engine is low in stability and reliability. Positioning rings and cavity labyrinth seals are arranged at the two ends of a testbed body, the outerring faces and the side end faces of the positioning rings are matched with a front cavity or a rear cavity in a high-precision mode, the positioning rings and the testbed body are sealed through thecavity labyrinth seals, circular beads are arranged on the inner side of the front cavity and the inner side of the rear cavity, the circular beads of the front cavity and the rear cavity and a middlecavity form a high-pressure chamber where a floating ring works, the floating ring is limited in the high-pressure chamber, hole channels are machined in the front cavity and the rear cavity and communicate with a channel of the floating ring, and eddy current displacement sensors are installed on the floating ring and a bearing pedestal. The rocket turbopump floating ring seal testing testbed isused for a rocket turbopump floating ring seal test.

Description

technical field [0001] The invention relates to a sealing test test bench, in particular to a test bench used for the sealing test of a floating ring of a rocket turbine pump, belonging to the field of aerospace technology. Background technique [0002] In modern industrial plant systems, due to the widespread use of fluid machinery, sealing plays a vital role. The design research of sealing problem is of great significance in the field of science and technology, especially for the design of rotating machinery such as aerospace engines. [0003] The turbo pump device of the liquid rocket engine provides low-temperature oxidant and fuel to the combustion chamber of the jet engine. A key technology in its design is to isolate the low-temperature fuel, so the sealing measures are related to the working efficiency and reliability of the rocket engine. In the harsh environment of high speed, high pressure difference, ultra-low temperature and ultra-high temperature in the rocket...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/96F04D15/00
CPCF02K9/96F04D15/0088
Inventor 张广辉刘占生陈晖封纪港赵经明
Owner HARBIN INST OF TECH
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