Analysis of Thermal ICE Protection Using Piccolo Tube

Volume 2, Issue 8, August 2017 International Journal of Innovative Science and Research Technology
ISSN No: - 2456 2165
Analysis of Thermal ICE Protection Using Piccolo

Tube
Karan Jain, Willy Warghese, Rohith Thangirala
Department of Aerospace
SRM University, Chennai(INDIA)
Abstract- In-flight icing is a major concern in aircraft aircraft nose and fuselage. Even a small ice formation on the
safety and a non-negligible source of incidents and wing leading edge would cause decrease in lift and decrease in
accidents, and is still a serious hazard today. It remains drag force .The various systems to avoid ice formations are
consequently a design and certification challenge for based on mechanical, chemical and thermal techniques. The
aircraft manufacturers. The aerodynamic performance of bleed air technique is the most popular in the aircraft industry.
an aircraft can indeed degrade rapidly when flying in icing A piccolo tube with a series of in line staggered holes is
conditions, leading to accidents. In-flight icing occurs when placed inside the leading end near to its inner surface. The hot
an aircraft passes through clouds containing super cooled bleed air from the engine compressor is passed through the
water droplets at or below freezing temperature. Droplets piccolo tube and it ejects from the piccolo tube holes in the
impinge on its exposed surfaces and freeze, causing form of high velocity jets that impinge on the inner surface to
roughness and shape changes that increase drag, decrease outer surface maintaining the wing leading edge hot enough to
lift and reduce the stall angle of attack, eventually avoid accretion of ice.
inducing flow separation and stall. This hazardous ice
accretion is prevented by the use of dedicated anti-icing On the other hand Icing wing tunnel testing is costly and
systems, among which hot- air-types are the most common limiting. Both these cases are suitable for analyzing a system
for aircraft. A widely used method in aviation Industry to but can hardly be used for design platform. Therefore, it is
overcome this problem is to employ a Hot-Air Anti-icing logical to benefit from CFD model to optimize anti icing
system owing to its simplicity, efficiency and reliability. systems before they are tested. Nevertheless fully coupled 3D
High temperature, hig pressure air from the engine stimulations are quite demanding in terms of computing
compressor is extracted and passed through a piccolo tube, resources.
and the distance between piccolo tube and wing inner
surface have strong influence on keeping the external
surface of the wing leading edge sufficiently hot to avoid II. EXPERIMENTAL METHODOLOGY
ice formation. In the present work, anti-icing scheme for a
typical aircraft wing of an airfoil shape, involving effect of
hot air jets from a piccolo tube, is investigated NACA 2412 airfoil was used for wing section. The profile was
numerically. The CAD model of the wing-piccolo tube decline with maximum camber of 2%chord length, maximum
assembly is generated using CATIA software and camber position at 40% chord length and maximum thickness
discretisation of the flow domain is being done using of 12% chord length a chord length of 1.5 m was selected. The
ANSYS software. wing leading edge was equipped with a bleed air system
consisting of a piccolo tube. The heated region extended to
I. INTRODUCTION 12% of chord on both upper surfaces. The piccolo tube had an
outer diameter of 22mm. The diameter jet hole was 9mm and
the spacing between adjacent holes was 7mm.
Design of the aircraft bleed-air ice protection systems involves
optimization of multiple geometric and flow of parameters
under constraints such as a system weight and bleed air
availability from the power plant at various flight regimes.
Geometric design parameters that have sufficient impact on
the bleed air ice protection system performance include airfoil
section, diffused shape, number of piccolo tube hole diameter,
hole pitch, hole circumferential parameter and hole pattern.
Ice formation on an aircraft structure occurs over the leading
edge of aircraft wings, lip of the intake duct and also on the
IJISRT17AG70 www.ijisrt.com 148

ISSN No: - 2456 2165
III. EXPERIMENTAL RESULTS

AND DISCUSSION
Case1-Hot air jets coming out of the piccolo tube arrangement

at -45 D to 45 Degree. The accelerated flow subsequently
lowered the static temperature and increased the cooling effect
on the upper surface. The hot ir from piccolo tube impinged
on the wing skin and circulated inside the diffuser region
before leaving through the upper and lower diffuser passages
formed between the inner liner and the wing skin.
Case 2-Hot air jets coming out of piccolo tube arrangement at

centre 0 degree. The temperature distribution along either side
of the chord line is more inform and the results appear to be
better and efficient when compared to case 1. Analysis results
it is evident that case 2 piccolo tube and wing inner surface
gives favorable temperature distribution on the outer surface
of the wing and the surface is sufficiently high to avoid ice
formation under flight condition.
Fig. 1.
Fig. 3.
IV. CONCLUSION
In case 1 temperature distribution was not that sufficient and

effective for removal of ice. From analysis it is found that in
case 1 maximum temperature distribution was 225k but
Fig. 2. overall temperature around the span was found to be 175k and
minimum temperature was 35k. But in case 2 maximum

ISSN No: - 2456 2165
temperature was 375k and minimum temperature was 25k and

this temperature is sufficient for ice removal.
REFERENCES
[1]. FAA Information for Operators 09005.

[2]. http://www.compositesworld.com/articles/787-
integrates-new-composite-wing-deicing-system.
[3]. http://www.boeing.com/commercial/aeromagazine/articl
es/qtr_4_07/article_02_4.html.
[4]. http://papers.sae.org/2009-01-3165/ | Capitalizing on the
Increased Flexibility that Comes from High Power
Density Electrothermal Deicing.
[5]. "How They Work: Ice Protection Systems". Aviation
Week. 2010.
[6]. "Electro- mechanical Deicing". Air & Space Magazine.
2004.
[7]. "CUTAWAY: P-8A Poseidon - A Boeing with boost of
bravado". Flight International. 2010.

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Volume 2, Issue 8, August 2017 International Journal of Innovative Science and Research Technology

ISSN No: - 2456 2165

Analysis of Thermal ICE Protection Using Piccolo

IJISRT17AG70 www.ijisrt.com 148

III. EXPERIMENTAL RESULTS

Case1-Hot air jets coming out of the piccolo tube arrangement

Case 2-Hot air jets coming out of piccolo tube arrangement at

In case 1 temperature distribution was not that sufficient and

IJISRT17AG70 www.ijisrt.com 149

temperature was 375k and minimum temperature was 25k and

[1]. FAA Information for Operators 09005.

IJISRT17AG70 www.ijisrt.com 150

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