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A coaxial liquid oxygen kerosene engine turbo pump structure

A technology for a kerosene pump and an engine, which is applied to the structure field of a coaxial liquid oxygen kerosene engine turbo pump, can solve the problems of high cost, large weight and space size, and a large number of turbo pump parts, and achieves safe operation, compact structure, The effect of reducing production, processing and testing costs

Active Publication Date: 2021-06-08
XIAN AEROSPACE PROPULSION INST
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  • Abstract
  • Description
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  • Application Information

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Problems solved by technology

[0003] The main purpose of the present invention is to solve the technical problems of large number of turbo pump parts, large weight and space size, and high cost, and provide a coaxial liquid oxygen kerosene engine turbo pump structure

Method used

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  • A coaxial liquid oxygen kerosene engine turbo pump structure
  • A coaxial liquid oxygen kerosene engine turbo pump structure
  • A coaxial liquid oxygen kerosene engine turbo pump structure

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Embodiment Construction

[0036] The technical solutions of the present invention will be clearly and completely described below in conjunction with the embodiments of the present invention and the accompanying drawings. Apparently, the described embodiments do not limit the present invention.

[0037] Such as Figure 1 to Figure 5 As shown, the present invention provides a coaxial liquid oxygen kerosene engine turbine pump structure, the kerosene pump is centered, the turbine and the oxygen pump are separated on both sides, and one turbine drives the oxygen pump and the kerosene pump at the same time, with compact structure and few parts, mainly composed of oxygen Pump, kerosene pump, turbine, seal between oxygen pump and kerosene pump, seal between turbine and kerosene pump.

[0038]The oxygen pump includes oxygen pump inlet pipe 4, oxygen pump inducer 5, oxygen pump guide sleeve 6, oxygen pump centrifugal wheel front seal ring 8, oxygen pump centrifugal wheel 9, oxygen pump housing 10, oxygen pump c...

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Abstract

The invention belongs to turbo pumps. In order to solve the technical problems of large number of turbo pump parts, large weight and space size, and high cost, a coaxial liquid oxygen kerosene engine turbo pump structure is provided, including a coaxially arranged oxygen pump, Kerosene pump and turbine; the oxygen pump and kerosene pump are sleeved on the turbine rotor of the turbine, and the kerosene pump is located between the oxygen pump and the turbine; the turbine and the kerosene pump are sealed by a leather cup; the oxygen pump and the kerosene pump Set two sets of end face seals and floating ring seals between them, the end face seals and floating ring seals are installed in the oxygen pump housing of the oxygen pump, and the two sets of end face seals are respectively located outside the two sets of floating ring seals. Due to the coaxial arrangement of the turbine, kerosene pump and oxygen pump, one turbine drives the kerosene pump and the oxygen pump at the same time. The structure is compact, which effectively reduces the number of parts, weight and space outline of the turbo pump, and reduces the production, processing and testing of the turbo pump. Cost, improved turbopump reliability.

Description

technical field [0001] The invention belongs to turbo pumps, in particular to a coaxial liquid oxygen kerosene engine turbo pump structure. Background technique [0002] As the core component of the launch vehicle engine, the turbo pump is driven by the turbine to pressurize the low-pressure liquid propellant components from the storage tank, and deliver the propellant to the main thrust chamber according to the parameters required by the engine system. Liquid oxygen kerosene is used as propellant in launch vehicles, which has the characteristics of high specific impulse, low cost, and convenient operation and maintenance, so it is widely used. However, the existing turbopump has a large number of components, which leads to a large weight and space size, and high cost. Contents of the invention [0003] The main purpose of the present invention is to solve the technical problems of large number of turbo pump components, large weight and space size, and high cost, and prov...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F04D1/06F04D29/10F04D29/12F04D29/22F04D29/42F04D29/58F02K9/46
CPCF02K9/46F04D1/06F04D29/106F04D29/126F04D29/225F04D29/426F04D29/588
Inventor 白东安付瑜许开富安莎刘军年赵瑞勇徐楠
Owner XIAN AEROSPACE PROPULSION INST
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