Test of rocket engine turbo pump performance under the occurrence of harsh cavitation
In the rocket engine turbo pump, the inducer is attached in front of the main impeller. The engine turbo pump is an important piece of machine that takes in liquid oxygen (boiling point of -183°C) and liquid hydrogen (boiling point of -253°C), which boil easily, and triggers a boost in the main impeller.
The Cryogenic Advanced Turbopump Test Stand facility uses liquid nitrogen, a cryogenic fluid (boiling point of -196°C ), to test the performance of the inducer and pump (inducer + main impeller) under the occurrence of harsh cavitation.
The liquid nitrogen test makes it possible to run a test in a wide range of temperatures (from the freezing point (-210°C) to close to the boiling point) by using a vacuum pump and temperature control mechanism.
|Department||Space Technology Directorate I|
|Installation location||Kakuda Space Center inducer|
|Inducer test||Test fluid: Liquid nitrogen
Maximum number of rotations: 35,000 rpm
Maximum flow rate: 180 liters/second
Maximum pressure: 4.0 MPa
Impeller diameter: approx. 150 mm
|Pump test||Test fluid: Liquid nitrogen
Maximum number of rotations: 22,000 rpm
Maximum flow rate: 50 liters/second
Maximum pressure: 20 MPa
Impeller diameter: approx. 170 mm
|Motor output/number of rotations||1,400kW/3,000rpm|
|Year of completion||FY 2003|