An exergy framework was developed taking into consideration a detailed analysis of the heat exchanger (HEX) (intercooler (IC)) component irreversibilities. Moreover, it was further extended to include an adequate formulation for closed systems, e.g., a secondary cycle (SC), moving with the aircraft. Afterward, the proposed framework was employed to study two radical intercooling concepts. The first proposed concept uses already available wetted surfaces, i.e., nacelle surfaces, to reject the core heat and contributes to an overall drag reduction. The second concept uses the rejected core heat to power a secondary organic Rankine cycle and produces useful power to the aircraft-engine system. Both radical concepts are integrated into a high bypass ratio (BPR) turbofan engine, with technology levels assumed to be available by year 2025. A reference intercooled cycle incorporating a HEX in the bypass (BP) duct is established for comparison. Results indicate that the radical intercooling concepts studied in this paper show similar performance levels to the reference cycle. This is mainly due to higher irreversibility rates created during the heat exchange process. A detailed assessment of the irreversibility contributors, including the considered HEXs and SC, is made. A striking strength of the present analysis is the assessment of the component-level irreversibility rate and its contribution to the overall aero-engine losses.

References

References
1.
Grönstedt
,
T.
,
Irannezhad
,
M.
,
Xu
,
L.
,
Thulin
,
O.
, and
Lundbladh
,
A.
,
2014
, “
First and Second Law Analysis of Future Aircraft Engines
,”
ASME J. Eng. Gas Turbines Power
,
136
(
3
), p. 031202.
2.
Zhao
,
X.
,
Thulin
,
O.
, and
Grönstedt
,
T.
,
2015
, “
First and Second Law Analysis of Intercooled Turbofan Engine
,”
ASME J. Eng. Gas Turbines Power
,
138
(
2
), p. 021202.
3.
Kotas
,
T. J.
,
1985
,
The Exergy Method of Thermal Plant Analysis
,
Butterworths
, London.
4.
Clarke
,
J. M.
, and
Horlock
,
J. H.
,
1975
, “
Availability and Propulsion
,”
J. Mech. Eng. Sci.
,
17
(
4
), pp.
223
232
.
5.
Evans
,
R. B.
,
1969
, “
A Proof that Essergy is the Only Consistent Measure of Potential Work
,”
Ph.D. thesis
, Dartmouth College, Hanover, NH.http://www.dtic.mil/dtic/tr/fulltext/u2/691899.pdf
6.
Brilliant
,
H. M.
,
1995
, “
Second Law Analysis of Present and Future Turbine Engines
,”
AIAA
Paper No. 95-3030.
7.
Roth
,
B.
,
McDonald
,
R.
, and
Mavris
,
D.
,
2000
, “
A Method for Thermodynamic Work Potential Analysis of Aircraft Engines
,”
AIAA
Paper No. 2002-3768.
8.
Thulin
,
O.
,
Grönstedt
,
T.
, and
Rogero
,
J.-M.
,
2015
, “
A Mission Assessment of Aero Engine Losses
,”
22nd International Symposium of Air Breathing Engines
(ISABE), Phoenix, AZ, Oct. 25–30, ISABE Paper No.
ISABE-2015-20121
.http://publications.lib.chalmers.se/publication/229215-a-mission-assessment-of-aero-engine-losses
9.
Thulin
,
O.
,
2017
,
On the Analysis of Energy Efficient Aircraft Engines
,” Ph.D. thesis, Department of Applied Mechanics, Fluid Dynamics, Chalmers University of Technology, Gothenburg, Sweden.
10.
Grieb
,
H.
,
2004
,
Projektierung Von Turboflugtriebwerken
,
Birkhauser
, Basel, Switzerland.
11.
Samuelsson
,
S.
,
Kyprianidis
,
K.
, and
Grönstedt
,
T.
,
2015
, “
Consistent Conceptual Design and Performance Modeling of Aero Engines
,”
ASME
Paper No. GT2015-43331.
12.
Kwan
,
P.-W.
,
Gillespie
,
D. R. H.
,
Stieger
,
R. D.
, and
Rolt
,
A. M.
,
2011
, “
Minimising Loss in a Heat Exchanger Installation for an Intercooled Turbofan Engine
,”
ASME
Paper No. GT2011-45814.
13.
Kyprianidis
,
K. G.
,
Rolt
,
A. M.
, and
Grönstedt
,
T.
,
2013
, “
Multidisciplinary Analysis of a Geared Fan Intercooled Core Aero-Engine
,”
ASME J. Eng. Gas Turbines Power
,
136
(
1
), p.
011203
.
14.
Zhao
,
X.
,
Grönstedt
,
T.
, and
Kyprianidis
,
K.
,
2013
, “
Assessment of the Performance Potential for a Two-Pass Cross Flow Intercooler for Aero Engine Applications
,”
21st International Symposium for Air Breathing Engines
(ISABE), Busan, South Korea, Sept. 9–13, ISABE Paper No.
ISABE-2013-1215
.https://www.researchgate.net/publication/259009545_Assessment_of_the_performance_potential_for_a_two-pass_cross_flow_intercooler_for_aero_engine_applications
15.
A'Barrow
,
C.
,
Carrotte
,
J. F.
,
Walker
,
A. D.
, and
Rolt
,
A. M.
,
2012
, “
Aerodynamic Performance of a Coolant Flow Off-Take Downstream of an Outlet Guide Vane
,”
ASME J. Turbomach.
,
135
(
1
), p.
011006
.
16.
Zhao
,
X.
, and
Grönstedt
,
T.
,
2015
, “
Aero Engine Intercooling Optimization Using a Variable Flow Path
,”
22nd International Symposium of Air Breathing Engines
(ISABE), Phoenix, AZ, Oct. 25–30, ISABE Paper No.
ISABE-2015-20018
.http://publications.lib.chalmers.se/records/fulltext/225382/local_225382.pdf
17.
Petit
,
O.
,
Xisto
,
C.
,
Zhao
,
X.
, and
Grönstedt
,
T.
,
2016
, “
An Outlook for Radical Aero Engine Intercooler Concepts
,”
ASME
Paper No. GT2016-57920.
18.
Kramer
,
B.
,
Smith
,
B.
,
Heid
,
J.
,
Noffz
,
G.
,
Richwine
,
D.
, and
Ng
,
T.
,
1999
, “
Drag Reduction Experiments Using Boundary Layer Heating
,”
AIAA
Paper No. 99-0134.
19.
ESDU International plc
,
1981
, “
Drag of Axisymmetric Cowls at Zero Incidence for Subsonic Mach Numbers
,” ESDU International plc, London.
20.
Perullo
,
C. A.
,
Mavris
,
D. N.
, and
Fonseca
,
E.
,
2013
, “
An Integrated Assessment of an Organic Rankine Cycle Concept for Use in Onboard Aircraft Power Generation
,”
ASME
Paper No. GT2013-95734.
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