0
Research Papers

Pressure Surge During Cryogenic Feedline Chilldown Process

[+] Author and Article Information
Gagan Agrawal

Liquid Propulsion Systems Centre, ISRO,
Thiruvananthapuram 695547, Kerala, India
e-mail: agl.gagan@gmail.com

S. Sunil Kumar

Liquid Propulsion Systems Centre, ISRO,
Thiruvananthapuram 695547, Kerala, India
e-mail: sunil_plamood@yahoo.com

Deepak Kumar Agarwal

Liquid Propulsion Systems Centre, ISRO,
Thiruvananthapuram 695547, Kerala, India
e-mail: dagarwal_iitk@yahoo.com

1Corresponding author.

Contributed by the Heat Transfer Division of ASME for publication in the JOURNAL OF THERMAL SCIENCE AND ENGINEERING APPLICATIONS. Manuscript received April 24, 2014; final manuscript received June 5, 2015; published online November 11, 2015. Assoc. Editor: P. K. Das.

J. Thermal Sci. Eng. Appl 8(1), 011005 (Nov 11, 2015) (9 pages) Paper No: TSEA-14-1082; doi: 10.1115/1.4030840 History: Received April 24, 2014

Cryogenic fluid entering a warm feedline absorbs heat and undergoes rapid flash evaporation leading to pressure surges, which can retard the flow inside the feedline. It may have serious repercussion in operation of the rocket engine during start up. Experimental and numerical studies are carried out to examine the effect of inlet pressure and initial feedline temperature on pressure surges. An analytical model using sinda/fluint software is developed to investigate this complex two-phase flow phenomenon including the various boiling regimes that exist during line chilling. The numerical study is carried out considering 1D flow through a cryogenic feedline of 2.47 m long and 0.01 m inner diameter with liquid nitrogen at 77.3 K as working fluid. Predictions are made for the inlet pressure in the range of 0.28–0.76 MPa and initial wall temperature of 200 K and 300 K. Subsequently, an experimental test rig is setup and the model is validated with the experimental data. The studies show that within the range of parameter considered, the magnitude of pressure surge increases exponentially with increase in inlet pressure and decreases with the prechilling of feedline.

Copyright © 2016 by ASME
Your Session has timed out. Please sign back in to continue.

References

Figures

Grahic Jump Location
Fig. 1

Schematic diagram of the experimental setup

Grahic Jump Location
Fig. 2

Flow and thermal model for cryogenic feedline chilling

Grahic Jump Location
Fig. 3

Pressure surge at 0.28 MPa inlet pressure

Grahic Jump Location
Fig. 4

Pressure surges at various inlet pressures

Grahic Jump Location
Fig. 5

Maximum surge pressure at various inlet pressures

Grahic Jump Location
Fig. 6

Time of occurrence of maximum surge pressure at various inlet pressures

Grahic Jump Location
Fig. 7

Comparison in numerical data and literature data of pressure surge

Grahic Jump Location
Fig. 8

Comparison in numerical data and in-house experimental data of pressure surge

Grahic Jump Location
Fig. 9

Pressure surge in feedline for various inlet pressure

Grahic Jump Location
Fig. 10

Surface and fluid temperature at line exit for inlet pressure of 0.45 MPa

Grahic Jump Location
Fig. 11

Vapor fraction at line exit for inlet pressure of 0.45 MPa

Grahic Jump Location
Fig. 12

Surface temperature at different locations for inlet pressure of 0.45 MPa

Grahic Jump Location
Fig. 13

Fluid velocity at line exit for inlet pressure of 0.45 MPa

Grahic Jump Location
Fig. 14

Wall temperature at line exit for different inlet pressure

Grahic Jump Location
Fig. 15

Wall temperature at line exit for different initial line temperature

Grahic Jump Location
Fig. 16

Pressure surge in feedline for various initial line temperatures

Tables

Errata

Discussions

Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In