A Numerical Study on the Simulation of Power-pack Start-up of a Staged Combustion Cycle Engine

Flow-induced vibration (FIV) is one of the main reasons for subsea piping failure, where subsea pipes, which typically carry multiphase flow, experience large fluctuating forces. These fluctuating forces can induce severe vibrations leading to premature piping failure. This paper presents a transient numerical study of a typical subsea M-shape jumper pipe that is carrying a gas-liquid multiphase flow subject to a slug frequency of 4.4 Hz, starting from rest to include the start-up effect as part of the study. 3-D numerical simulations were used to capture the fluid-structure interaction (FSI) and estimate pipe deformations due to fluctuating hydrodynamic forces. In this paper, two FSI approaches were used to compute the pipe deformations, two-way coupled and one-way decoupled. Analysis of the results showed that decoupled (one-way) FSI approach overestimated the peak pipe deformation by about 100%, and showed faster decay of fluctuations than coupled (two-way) FSI analysis. The assessment of resonant risk due to FIV is also discussed.

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CFD analysis of axial pump of lox booster turbo pump for a staged combustion cycle based rocket engine

Indian Journal of Cryogenics ◽

10.5958/2349-2120.2017.00014.0 ◽

2017 ◽

Vol 42 (1) ◽

pp. 91

Author(s):

Arpit Mishra ◽

Parthasarathi Ghosh

Keyword(s):

Rocket Engine ◽

Cfd Analysis ◽

Staged Combustion ◽

Axial Pump ◽

Turbo Pump ◽

Combustion Cycle

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A review of the Mark 48-F, 3.50 pitch diameter, 2-stage reaction turbine designed for the staged combustion cycle requirements of an advanced space engine

10.2514/6.1976-688 ◽

1976 ◽

Author(s):

S. MACALUSO

Keyword(s):

Staged Combustion ◽

Combustion Cycle

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Numerical study of two-dimensional moist symmetric instability

Advances in Geosciences ◽

10.5194/adgeo-17-1-2008 ◽

2008 ◽

Vol 17 ◽

pp. 1-4 ◽

Cited By ~ 4

Author(s):

M. Fantini ◽

P. Malguzzi

Keyword(s):

Numerical Study ◽

Finite Amplitude ◽

Two Dimensional ◽

Initial State ◽

Linear Mode ◽

Equivalent Potential ◽

Start Up ◽

Set Up ◽

Symmetric Instability ◽

Amplitude Evolution

Abstract. The 2-D version of the non-hydrostatic fully compressible model MOLOCH developed at ISAC-CNR was used in idealized set-up to study the start-up and finite amplitude evolution of symmetric instability. The unstable basic state was designed by numerical integration of the equation which defines saturated equivalent potential vorticity qe*. We present the structure and growth rates of the linear modes both for a supersaturated initial state ("super"-linear mode) and for a saturated one ("pseudo"-linear mode) and the modifications induced on the base state by their finite amplitude evolution.

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Combustion Test of Oxidizer-Rich Single Triplex Injector Preburner for Staged Combustion Cycle Rocket Engine

Volume 1A: Symposia, Part 2 ◽

10.1115/ajkfluids2015-09287 ◽

2015 ◽

Author(s):

Su-Ji Lee ◽

In-Sang Moon ◽

Il-Yoon Moon ◽

Seong-Up Ha

Keyword(s):

Combustion Chamber ◽

Dynamic Pressure ◽

Rocket Engine ◽

Rocket Engines ◽

Fuel Injector ◽

Staged Combustion ◽

Combustion Pressure ◽

The Republic ◽

Combustion Tests ◽

Combustion Cycle

In the Republic of Korea, research on staged-combustion cycle liquid propellant rocket engines (LPRE) is proceeding to improve efficiency of rocket engines. Recently oxidizer-rich preburner using single triplex injector is developed in relation to the main injector development and combustion tests have been performed. This preburner is designed to operate in nominal conditions with the combustion pressure of 10 MPa, OF ratio of 60. For a stable ignition, LOx is fed in two steps. Triethylaluminum-Triethylborane (TEAB) is used as hypergolic fuel for ignition, supplied through a fuel injector. Despite the small amount of fuel flow rate and high pressure condition, the combustion pressure was stably maintained around 10 MPa as designed. As a result of Fast Fourier Transform (FFT) of the combustion chamber dynamic pressure, 1L mode frequencies related to the acoustic instability and hydraulic resistance exist in the combustion chamber. But their amplitudes are less than 1% of the combustion pressure and it does not affect the combustion. Therefore combustion test is stably completed. In the near future, coupled tests with uni-element triplex injector preburner and uni-element gas/liquid injector main combustion chamber will be carried out.

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509 Numerical Study on Transient Flow Characteristics in the Start-up Process of a Rocket Nozzle

The Proceedings of Conference of Kyushu Branch ◽

10.1299/jsmekyushu.2010.63.175 ◽

2010 ◽

Vol 2010.63 (0) ◽

pp. 175-176

Author(s):

Toshiaki Setoguchi ◽

Shigeru Matsuo ◽

Tokitada Hashimoto ◽

Junji Nagao ◽

Heuy-Dong Kim

Keyword(s):

Transient Flow ◽

Numerical Study ◽

Flow Characteristics ◽

Rocket Nozzle ◽

Start Up

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Application of the Principle of Reciprocity to Flexible Rotor Balancing

Journal of Mechanical Design ◽

10.1115/1.3256347 ◽

1982 ◽

Vol 104 (2) ◽

pp. 329-333 ◽

Cited By ~ 2

Author(s):

M. S. Darlow ◽

A. J. Smalley

Keyword(s):

Numerical Study ◽

Influence Coefficient ◽

Theoretical Discussion ◽

Vibration Level ◽

Flexible Rotor ◽

Stabilization Time ◽

Vibration Sensors ◽

Start Up ◽

Desirable Feature ◽

Rotor Balancing

The least desirable feature of most flexible rotor balancing procedures is the considerable number of trial mass runs required. This is of particular importance in the balancing of machines which require a substantial stabilization time during start-up. Using an adaptation of the principle of reciprocity, it is possible to significantly reduce the required number of trial mass runs for certain rotors when using either influence coefficient balancing or the Unified Balancing Approach. When applied to flexible rotor balancing, the principle of reciprocity states that, given two rotor axial locations, A and B (at which both balancing planes and vibration sensors are located), the influence coefficient relating the vibration level at A to the unbalance at B is identical to that relating the vibration level at B to the unbalance at A. This is true even in the presence of damping. This paper begins with a theoretical discussion of the principle of reciprocity and its application to flexible rotor balancing. The particular means by which reciprocity can be applied to improve the influence coefficient and Unified Balancing Approach procedures are then described in detail. A numerical study was conducted to verify this application of reciprocity, as well as to investigate any possible limitations. The results of this study are reported along with those of a similar experimental study using two substantially different test rotors.

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