Topic
Pump inducer
About: Pump inducer is a research topic. Over the lifetime, 78 publications have been published within this topic receiving 1287 citations.
Papers published on a yearly basis
Papers
TL;DR: In this paper, a liquid oxygen turbopump has been developed for the main engine (LE-7) of the H-II rocket, which is the next generation of Japanese launch vehicle.
Abstract: A liquid oxygen turbopump has been developed for the main engine (LE-7) of the H-II rocket. The LE-7 LOX pump requires an inducer with quite high suction performance and high head, because a low-speed and low-pressure pump is not used ahead of the main pump in the LE-7 engine. The inducer was designed using the customary method, and its hydraulic and mechanical performances were investigated in tests of LE-7 LOX turbopumps. The original combination of an inducer and an inducer housing satisfied the required hydraulic performance criteria. However, this combination was found to result in supersynchronous shaft vibrations due to rotating cavitation which occurred in the inducer. This problem was almost completely solved by a simple modification of the inducer upstream housing. Furthermore, the rotating cavitation of the present inducer was investigated using a new theory of such cavitation. I. Introduction A LIQUID oxygen turbopump has been developed for the main engine (LE-7) of the H-II rocket, the next generation of Japanese launch vehicle. This turbopump requires a high-flow, high-pressure liquid oxygen pump. Because a low-speed, low-pressure pump is not used ahead of the main pump in the LE-7 engine, it is very important to operate the main pump at higher speed to obtain a smaller-size, lighterweight turbopump. The operational speed of the present turbopump was restricted by the suction performance of the main pump inducer. In this article, we report both the design and test results of the inducer. The main pump of the LE-7 LOX turbopump has a singlestage centrifugal impeller with an inducer. 1 The inducer is characterized by a low flow coefficient, a small inlet angle, a sharp leading edge, etc., to achieve higher suction performance. The inducer was designed using the customary method.2-3
149 citations
6 Jul 1992
TL;DR: In this paper, a liquid oxygen turbopump has been developed for the main engine (LE-7) of the H-II rocket, which is the next generation of Japanese launch vehicle.
Abstract: A liquid oxygen turbopump has been developed for the main engine (LE-7) of the H-II rocket. The LE-7 LOX pump requires an inducer with quite high suction performance and high head, because a low-speed and low-pressure pump is not used ahead of the main pump in the LE-7 engine. The inducer was designed using the customary method, and its hydraulic and mechanical performances were investigated in tests of LE-7 LOX turbopumps. The original combination of an inducer and an inducer housing satisfied the required hydraulic performance criteria. However, this combination was found to result in supersynchronous shaft vibrations due to rotating cavitation which occurred in the inducer. This problem was almost completely solved by a simple modification of the inducer upstream housing. Furthermore, the rotating cavitation of the present inducer was investigated using a new theory of such cavitation. I. Introduction A LIQUID oxygen turbopump has been developed for the main engine (LE-7) of the H-II rocket, the next generation of Japanese launch vehicle. This turbopump requires a high-flow, high-pressure liquid oxygen pump. Because a low-speed, low-pressure pump is not used ahead of the main pump in the LE-7 engine, it is very important to operate the main pump at higher speed to obtain a smaller-size, lighterweight turbopump. The operational speed of the present turbopump was restricted by the suction performance of the main pump inducer. In this article, we report both the design and test results of the inducer. The main pump of the LE-7 LOX turbopump has a singlestage centrifugal impeller with an inducer. 1 The inducer is characterized by a low flow coefficient, a small inlet angle, a sharp leading edge, etc., to achieve higher suction performance. The inducer was designed using the customary method.2-3
133 citations
TL;DR: In this paper, the authors present full 3D numerical simulations and experimental investigations of the cavitating flow through three axial inducers, identified by the tip blade angle at the leading edge β 1T =8, 10, and 13 deg.
Abstract: The paper presents full 3D numerical simulations and experimental investigations of the cavitating flow through three axial inducers. These inducers are identified by the tip blade angle at the leading edge β 1T =8, 10, and 13 deg. The numerical and experimental investigations were carried out at the LEMFI laboratory (Laboratoire d'Energetique et de Mecanique de Fluides Interne) of the ENSAM-Paris center (Ecole rationale Superieure d'Arts et Metiers). A review of the cavitating regime modeling and the cavitation homogeneous model used for this paper's calculations is first presented. The numerical model is based on a combination of the multiphase flow equations with a truncated version of the Rayleigh-Plesset model predicting the complicated growth and collapse processes of bubbles. The mass transfers due to cavitation are source/sink terms in continuity equations of the liquid and vapor phases
98 citations
TL;DR: In this article, a simple modie cation of the inducer upstream housing almost completely extinguished the shaft vibrations caused by rotating cavitation in a liquid oxygen (LOX) turbopump for the H-II rocket.
Abstract: Research on rotating cavitation progressed during the development of a liquid oxygen (LOX) turbopump for the LE-7 engine of the H-II rocket In some ranges of cavitation numbers, supersynchronous shaft vibrations were observed in the LE-7 LOX main pump inducer From a comparison with the results of our previous studies it was concluded that such shaft vibrations were caused by rotating cavitation in the inducer A simple modie cation of the inducer upstream housing almost completely extinguished such shaft vibrations Some characteristics of rotating cavitation have been fairly well elucidated However, we were not able to fully explain the mechanism of the ine uence of the simple modie cation of the inducer upstream housing on the rotating cavitation We thus commenced further experimental studies to investigate rotating cavitation in more detail In the present study, some visual observations of rotating cavitation were conducted using the same inducer test facility as that used in our previous work
91 citations
TL;DR: In this paper, the numerical simulation of cavitating flows in turbomachinery is studied at the Turbomachinery and Cavitation team of LEGI (Grenoble - France) in collaboration with the French space agency (CNES) and the rocket engine division of SNECMA Moteurs.
Abstract: The numerical simulation of cavitating flows in turbomachinery is studied at the Turbomachinery and Cavitation team of LEGI (Grenoble - France) in collaboration with the French space agency (CNES) and the rocket engine division of SNECMA Moteurs. A barotropic state law is proposed to model the cavitation phenomenon and this model has been integrated in the commercial CFD code Fine/TurboTM, developed and commercialized by Numeca International. The numerical aspects of the work are mainly focused on numerical stability and reliability of the algorithm, when introducing large density variations through the strongly non linear barotropic state law. This research conducted first to changes in the way preconditioning parameters are calculated. Internal flows in turbomachinery have been deeply investigated. A methodology allowing the numerical simulation of the head drop induced by the development of cavitation has been proposed on the basis of computations in inducers and centrifugal pumps. These simulations have allowed the characterization of the mechanisms leading to the head drop and the visualization of the effects of the development of cavitation on internal flows.
84 citations
Related Topics (5)
Performance Metrics
| Year | Papers |
|---|---|
| 2021 | 1 |
| 2020 | 1 |
| 2019 | 1 |
| 2017 | 2 |
| 2015 | 1 |
| 2013 | 1 |