CEC Abstracts in PDF format (as of 7/3/07) - CEC-ICMC 2013

CEC 2007 - Abstracts
C2-C-04 An aerospace miniature pulse tube cryocooler at
80K
H.L. Chen, L.W. Yang, J.H. Cai, J.T. Liang, Y. Zhou,
Technical Institute of Physics and Chemistry, CAS.
An engineering model of a miniature pulse tube cryocooler is
designed for space application. Coaxial configuration of the cold
finger is convenient to connect with the aim element and improves
integration. A series of jointing cooler products are manufactured and
tested. The overall mass of the whole cooler system is around 3.5kg.
The product coolers can provide 0.7W cooling capacity at 80K within
40W input electric power, while the experimental ones can proveide
more than 0.8W cooling capacity. To make a product for space
application, intense structure, light weight and small size are needed,
so different materials and structures et al. decrease the cooling
performance more or less. Reliability of the cooler working
continously is tested. Also, the magnetic field of the compressor and
anti-shake ability of the system has been examined.
C2-C-05 Investigation of a 500Hz heat-driven pulse tube
cooler by using etched foil regenerator
S.L. Zhu, Graduate University of Chinese Academy of
Sciences; E.C. Luo, Technical Institute of Physics and
Chemistry, CAS; W. Dai, Technical Institute of
Physics and Chemistry,CAS.
A thermoacoustically-driven high frequency pulse tube cooler has the
advantage of being compact, which has good potential of using for
aerospace cooling. This article presents a pulse tube cooler driven by a
traveling-wave thermoacoustic engine with a working frequency
around 500 Hz. As operating frequency increases, a traditional screenpacked
regenerator is limited by the requirement of smaller wire
diameter and higher mesh number of the screens. In this pulse tube
cooler, however, we have used the etched foil regenerator instead of
the screen-packed regenerator to decrease flowing loss, which shows
more important impact on the global performance of the whole system
when the operating frequency goes up to 500Hz. Experiments has
been conducted to investigate the characteristics of the pulse tube,
which includes the structure parameters of the novel regenerator and
the operating parameters including mean pressure, inlet pressure ratio,
inertance tube phase shifter. Numerical simulation results are also
made and compared with the experiment results in the same condition.
This work was supported by the Natural Science Foundation of
China(Grant No.50625620)
C2-C-06 Performance of a two stage Stirling cryocooler
for space applications
V.K. Bhojwani, M.D. Atrey, S.L. Bapat, Indian
Institute of Technology Bombay, Mumbai, India; K.G.
Narayankhedkar, Veermata Jijabai Technological
Institute, Mumbai, India.
A two-stage, split type Stirling cryocooler with capacity of 2 W at 100
K and 0.5 W at 50 K is designed. Second order cyclic analysis is used
to decide the final geometry of the unit. The compressor with opposed
pistons configuration is developed. Flexure stacks suspended piston
and displacer are used. Moving coil linear motor is developed.
Sensors are installed for measuring strokes of pistons and displacer;
and pressure at the outlet of the compressor. 10 channel oscilloscope
provides the variations of parameters. The load tests indicated that the
cooling capacities are close to the design values. The power input for
the compressor is 110 W as against 69 W predicted by the analysis.
The experimental no load temperature for the stage I is observed to be
close to the predicted temperature. Two identical expanders are
developed to check the repeatability. For expander I, the temperatures
attained for a load of 2 W on stage I and 0.5 W on stage II are 106 K
and 74 K respectively with a power input of around 110 W. The
corresponding values for expander II are 128 K, 66.7 K with a power
input of 105.6 W.
The authors thank Indian Space Research Organisation for financial
support.
C2-C-07 A model for the parametric analysis and
optimization of inertance tube pulse tube refrigerators
C Dodson, A Razani, AFRL/VSSS-UNM; A Lopez,
UNM/Sandia National labs; T Roberts, AFRL/VSSS.
A first order model developed for the design analysis and optimization
of Inertance Tube Pulse Tube Refrigerators (ITPTRs) is integrated
with the code NIST REGEN 3.2 capable of modeling the regenerative
heat exchangers used in ITPTRs. The model is based on the solution
of simultaneous non-linear differential equations representing the
inertance tube, an irreversibility parameter model for the pulse tube,
and REGEN 3.2 to simulate the regenerator. The integration of
REGEN 3.2 is accomplished by assuming a sinusoidal pressure wave
at the cold side of regenerator. In this manner the computational
power of REGEN 3.2 is conveniently used to reduce computational
time required for parametric analysis and optimization of ITPTRs.
The exergy flow and exergy destruction (irreversibility) of each
component of ITPTRs is calculated and the effect of important system
parameters on the second law efficiency of the refrigerators is
presented.
C2-C-08 Reliability Growth of Stirling-Cycle Coolers at
L-3 CE
D.T. Kuo, A.S. Loc, Q.K. Phan, L-3 Communications -
Cincinnati Electronics.
L-3 Communication is conducting a reliability growth program to
extend the life of tactical Stirling-cycle cryocoolers. The continuous
product improvement processes consist of testing production coolers
to failure, determining the root cause, incorporating improvements
and verification. The most recent life test data for the 0.6-Watt Cooler
(Model B600C), The 1.5-Watt Cooler (Model B1500E), and the Gas
Bearing 1.0-Watt Cooler (Model GB1000E) are presented. From the
life test data, sets of empirical constants are derived for life prediction,
for any operating condition using the Watt-Hour approach. The data
presented here extends the boundary of life data in previous papers
from the authors.
C2-C-09 Performance Optimization of L-3 CE 0.6-Watt
Linear Cooler
D.T. Kuo, A.S. Loc, L-3 Communication - Cincinnati
Electronics.
Tactical FLIR are placing increasing demand for cryocoolers to
deliver more performance without commensurate size and weight
allowances. L-3 CE has re-optimized the design of its 0.6-Watt cooler
to provide twice the refrigeration lift without significant changes to
weight and size. This paper presents the performance characteristics
of the re-optimized cooler model B610.
C2-D Large Scale Aerospace Test Facilities
C2-D-01 Large-Scale Test Facility for Advanced
Cryogenic and Energy Technology Development
W.H. Hatfield, Sierra Lobo, Inc.; D.E. Taylor, J.P.
Sass, NASA KSC.
NASA has completed initial construction and verification testing of
the Integrated Systems Test Facility (ISTF) Cryogenic Testbed. The
ISTF is located at Complex 20 at Cape Canaveral Air Force Station,
Florida. The remote and secure location is ideally suited for the
following functions: (1) development testing of advanced cryogenic
component technologies, (2) development testing of concepts and
processes for entire ground support systems designed for servicing
large launch vehicles, and (3) commercial-sector testing of cryogenicand
energy-related products and systems. The Cryogenic Testbed
consists of modular fluid distribution piping and storage tanks for
liquid oxygen/nitrogen (56,000 gal) and liquid hydrogen (66,000 gal).
Storage tanks for liquid methane (41,000 gal) and Rocket Propellant 1
(37,000 gal) are also specified for the facility. A state-of-the-art
blastproof test command and control center provides capability for
remote operation, video surveillance, and data recording for all test
areas.
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