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Aluminum and Alloy


Aluminium Alloys(orAluminum Alloys; seespelling differences) arealloysin whichAluminium(Al) is the predominant metal. The typical alloying elements areCopper, Magnesium, Manganese, Silicon, Tin And Zinc.

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Approx. Rs 52 / Square Feet(s) Get Latest Price

Specifications of Aluminum Checker Plate (Aluminum chequer plate,Aluminum checkered plate)Aluminum Checker Plate aslo named as Aluminum chequer plate,Aluminum checkered plate.It is easy to fabricate and its raised diamond ,bar,pointer,lug pattern provides good slip resistance.Which has good forming, drilling and welding abilityis and widely used in decorative, shipbuilding and architectural applications.

1 Grade:1060, 1100, 3003, 3105, 5052, 5083, 5754, 6061 etc.
2 Thickness: 1mm-6mm
3 Width: 2200mm max.
4 Length: 12000mm max.
5 Temper:H14/H154 H24/H254 H26/H274 H18/H194 H32/H334 etc.
6 Checker height: 1.0mm-1.5mm
7 Checker length: 35mm-50mm
8 Accept customization
Features of Aluminum Checker Plate (Aluminum chequer plate,Aluminum checkered plate)1)Light in weight
2)Convenient assembling
3)Disassembling
4)Antiskid
Pattern of Aluminum Checker Plate (Aluminum chequer plate,Aluminum checkered plate) 1) big 5 bar
2) small 5 bar
3) diamond
4) 3 bar
5) pointer
etc.

Additional Information:
  • Minimum Order Quantity: 32 Square Feet(s)

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While climbing on the success ladder, it has become increasingly important for us to deliver precisely tested and high grade assortment of Aluminum 24345. It is used for high strength parts in aircraft and machinery, including gears and bolts and for security vans where strength is critical. The offered range is manufactured using high grade raw material and contemporary technology.  We assure our clients that our range is quality tested on predefined parameters, in order to meet industry set standards. Apart from this our prestigious clients can avail these alloys, as per their needs, at highly competitive price.

Features:

  • Durability
  • Sturdy construction
  • Corrosion-resistance

Specifications:
Weight %SiFeCuMnCrMgNiZnTi + ZrTi
IS 243450.50-0.900.50 max3.9-5.00.4-1.20.10 max0.2-0.80.10 max0.25 max0.20 max0.15 max

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With sincere intentions to preserve and uplift our reputation in the market, we bring forth a distinguished assortment of Aluminum 6063. It is an aluminum alloy, with magnesium and silicon as the alloying elements. Our offered alloy is manufactured using utmost-grade raw material and cutting-edge technology in compliance with defined quality standards. The offered alloy is extensively used in various industrial applications. Keeping in mind the diverse requirements of our clients, we provide this alloy in various sizes and designs and at affordable prices.

Features:

  • Durable finish standards
  • Rust resistance
  • Sturdiness 

Other Details:

  • Silicon minimum 0.2%, maximum 0.6% by weight
  • Iron no minimum, maximum 0.35%
  • Copper no minimum, maximum 0.10%
  • Manganese no minimum, maximum 0.10%
  • Magnesium minimum 0.45%, maximum 0.9%
  • Chromium no minimum, maximum 0.10%
  • Zinc no minimum, maximum 0.10%
  • Titanium no minimum, maximum 0.10%
  • Other elements no more than 0.05% each, 0.15% total
  • Remainder Aluminium

Mechanical Properties:

6063-O:
 
  • Un-heat-treated 6063 has maximum tensile strength no more than 19,000 psi (131 Mpa), and no specified maximum yield strength
  • The material has elongation (stretch before ultimate failure) of 18%

6063-T1:
 
  • T1 temper 6063 has an ultimate tensile strength of at least 17,000 psi (117 MPa) in thicknesses up to 0.5-inch (13 mm), and 16,000 psi (110 MPa) from 0.5 to 1.0-inch (25 mm) thick, and yield strength of at least 9,000 psi (62 MPa) in thickness up to 0.5-inch (13 mm) and 8,000 psi (55 MPa) from 0.5 to 1.0-inch (25 mm) thick. It has elongation of 12%

6063-T4:
 
  • T4 temper 6063 has an ultimate tensile strength of at least 19,000 psi (131 MPa) in thicknesses up to 0.5-inch (13 mm), and 18,000 psi (124 MPa) from 0.5 to 1.0-inch (25 mm) thick, and yield strength of at least 10,000 psi (69 MPa) up to 0.5-inch (13 mm) and 9,000 psi (62 MPa) from 0.5 to 1.0-inch (25 mm). It has elongation of 14%

6063-T5:
 
  • T5 temper 6063 has an ultimate tensile strength of at least 20,000 psi (152 MPa) in thicknesses up to 0.5-inch (13 mm), and 19,000 psi (145 MPa) from 0.5 to 1.0-inch (25 mm) thick, and yield strength of at least 14,000 psi (110 MPa) up to 0.5-inch (13 mm) and 13,000 psi (103 MPa) (from 0.5 to 1.0-inch (25 mm). It has elongation of 8%

6063-T6:
 
  • T6 temper 6063 has an ultimate tensile strength of at least 28,000 psi (196 MPa) and yield strength of at least 23,000 psi (165 MPa)
  • In thicknesses of 0.124-inch (3.1 mm) or less, it has elongation of 8% or more; in thicker sections, it has elongation of 10%

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With the endorsement of our adept and seasoned professionals, we are engaged in offering a commendable range of Aluminum 63400. It is mostly used in extruded shapes for architecture, particularly window frames, door frames, roofs, and sign frames. It is typically produced with very smooth surfaces fit for anodizing. The offered alloy is manufactured by making use of high grade raw material and leading technology in synchronization with the set industrial norms. In line with clients' variegated requirements, we offer the entire range in various customized options. Moreover, clients can avail the entire range from us at industrial leading prices.

Features:

  • Precisely design
  • Rust proof
  • Durability

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In line with clients' diverse requirements across the country, we are offering an excellent range of Aluminum HE 9.  Extensively used for architecture, particularly window frames, door frames, roofs, and sign frames, it is typically produced with very smooth surfaces fit for anodizing. This alloy is manufactured using superior quality raw material and the latest technology by our skilled professionals. Being a quality-oriented organization, we assure our clients that this alloy is excellent on counts of durability and quality.

Features:

  • Sturdy structure
  • Excellent finish
  • Rust resistance

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Introduction

Aluminum alloys tend to lose their strength when they are exposed to temperatures of about 200-250°C. However, their strength increases at subzero temperatures. They have high corrosion resistance.

The following datasheet will discuss in detail about the aluminum 6351 alloy.

Chemical Composition

The chemical composition of the aluminum 6351 alloy is tabulated below.

ElementContent (%)
Aluminum, Al97.8
Silicon, Si1
Manganese, Mn0.6
Magnesium, Mg0.6
Physical Properties

The following table shows the physical properties of the aluminum 6351 alloy.

PropertiesMetricImperial
Density2.6-2.8 g/cc0.0939- 0.101 lb/in3
Mechanical Properties

The mechanical properties of the aluminum 6351 alloy are outlined in the following table.

PropertiesMetricImperial
Tensile strength250 MPa36260 psi
Yield strength150 MPa21756 psi
Shear strength200 MPa29008 psi
Fatigue strength90 MPa13054 psi
Elastic modulus70-80 GPa10153-11603 ksi
Poisson's ratio0.0330.033
Elongation20%20%
Hardness9595
Thermal Properties

The thermal properties of the aluminum 6351 alloy are given in the following table.

PropertiesConditions
T (ºC)Treatment
Thermal conductivity176 W/m-K25T6
Other Designations

Other designations equivalent to the aluminum 6351 alloy include ASTM B221.


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Introduction Aluminum alloys tend to lose their strength when they are exposed to temperatures of about 200-250°C. However, their strength increases at subzero temperatures. They have high corrosion resistance.
The following datasheet will discuss in detail about the aluminum 64430 alloy.
Chemical Composition The chemical composition of the aluminum 64430 alloy is tabulated below.
Element Content (%)Aluminum, Al 97.8Silicon, Si 1Manganese, Mn 0.6Magnesium, Mg 0.6Physical Properties The following table shows the physical properties of the aluminum 64430 alloy.
Properties Metric Imperial Density 2.6-2.8 g/cc 0.0939- 0.101 lb/in3Mechanical PropertiesThe mechanical properties of the aluminum 64430 alloy are outlined in the following table.
Properties Metric Imperial Tensile strength 250 MPa 36260 psiYield strength 150 MPa 21756 psiShear strength 200 MPa 29008 psiFatigue strength 90 MPa 13054 psiElastic modulus 70-80 GPa 10153-11603 ksiPoisson's ratio 0.033 0.033Elongation 20% 20%Hardness 95 95Thermal PropertiesThe thermal properties of the aluminum 64430 alloy are given in the following table.
Properties ConditionsT (ºC) TreatmentThermal conductivity 176 W/m-K 25 T6

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Introduction Aluminum alloys tend to lose their strength when they are exposed to temperatures of about 200-250°C. However, their strength increases at subzero temperatures. They have high corrosion resistance.
The following datasheet will discuss in detail about the aluminum HE 30 alloy.
Chemical Composition The chemical composition of the aluminum HE 30 alloy is tabulated below.
Element Content (%)Aluminum, Al 97.8Silicon, Si 1Manganese, Mn 0.6Magnesium, Mg 0.6Physical Properties The following table shows the physical properties of the aluminum HE 30 alloy.
Properties Metric Imperial Density 2.6-2.8 g/cc 0.0939- 0.101 lb/in3Mechanical Properties The mechanical properties of the aluminum HE 30 alloy are outlined in the following table.
Properties Metric Imperial Tensile strength 250 MPa 36260 psiYield strength 150 MPa 21756 psiShear strength 200 MPa 29008 psiFatigue strength 90 MPa 13054 psiElastic modulus 70-80 GPa 10153-11603 ksiPoisson's ratio 0.033 0.033Elongation 20% 20%Hardness 95 95Thermal PropertiesThe thermal properties of the aluminum HE 30 alloy are given in the following table.
Properties ConditionsT (ºC) TreatmentThermal conductivity 176 W/m-K 25 T6

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High strength alloys with excellent machinability widely used in aircraft. Have limited formability and only fair corrosion resistant in the heat treated condition. Not recommended for fusion welding. Used for high strength parts in aircraft and machinery, including gears and bolts and for security vans where strength ids critical. It has a tendency to allow the removal of a greater volume of metal in a single operation for an equipment standard of finish than 6082. Durability, however, is lower and needs a protection coating. Machines better in solution treated condition than fully heat treated. Used for machined parts where these characteristics are critical.

 
Aluminium Alloy 2014A
Technical Data Sheet
 
Chemical Composition Limits
Weight%AlSiFeCuMnCrMgNiZnTi+ZrTiOther EachOther Total
2014a AECMARem0.50 - 0.900.50 max3.9 - 5.00.4-1.20.10 max0.2-0.80.1 max0.25 max0.20 max0.15 max0.05 max0.15 max
2014 USARem0.50-1.200.7 max3.9 - 5.00.4 - 1.20.10 max0.2-0.8-0.25 max-0.15 max0.05 max0.15 max

Aluminium Alloy 2014 (2014 A) is a copper based alloy with very high strength together with excellent machining characteristics. Alloy 2014 is commonly used in many aerospace structural applications due to its high strength. Other applications include military vehicles, bridges, weapons manufacture and structural applications.


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High strength alloys with excellent machinability widely used in aircraft. Have limited formability and only fair corrosion resistant in the heat treated condition. Not recommended for fusion welding. Used for high strength parts in aircraft and machinery, including gears and bolts and for security vans where strength ids critical. It has a tendency to allow the removal of a greater volume of metal in a single operation for an equipment standard of finish than 6082. Durability, however, is lower and needs a protection coating. Machines better in solution treated condition than fully heat treated. Used for machined parts where these characteristics are critical.

DESCRIPTION

Alloy 2024 was the first Al-Cu-Mg alloy to have a yield strength approaching 50,000-psi and generally replaced 2017-T4 (Duralumin) as the predominant 2XXX series aircraft alloy. With its relatively good fatigue resistance, especially in thick plate forms, alloy 2024 continues to be specified for many aerospace structural applications. 2024 varient alloys, such as higher purity 2124 and 2324, with improvements in strength and other specific characteristics, have also found application in critical aircraft structures. An improved sheet alloy for fuselage applications was introduced in 1991. Alloy 2024 is available in bare and alclad sheet and plate product forms in the annealed state and several tempers of T3, T4, and T8 types.

APPLICATIONS Alloy 2024 plate products are used in fuselage structurals, wing tension members, shear webs and ribs and structural areas where stiffness, fatigue performance and good strength are required. Sheet products, usually alclad, are used extensively in commercial and military aircraft for fuselage skins, wing skins and engine areas where elevated temperatures to 250°F (121°C) are often encountered.

CHEMICAL COMPOSITION LIMITS (WT.%)
Si . . . 0.50
Zn  . . 0.25
Fe. . . 0.50
Ti . . . 0.15
Cu . . 3.8-4.9
Mn . . 0.30-0.9
Mg . . 1.2-1.8 
Cr. . . 0.10 
Others, each . . 0.05 
Others, total . . 0.15
Balance, Aluminum 

Note: Value maximum if range not shown

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High strength alloys with excellent machinability widely used in aircraft. Have limited formability and only fair corrosion resistant in the heat treated condition. Not recommended for fusion welding. Used for high strength parts in aircraft and machinery, including gears and bolts and for security vans where strength ids critical. It has a tendency to allow the removal of a greater volume of metal in a single operation for an equipment standard of finish than 6082. Durability, however, is lower and needs a protection coating. Machines better in solution treated condition than fully heat treated. Used for machined parts where these characteristics are critical.

Data Sheet:

Aluminium Alloy H15 HE 15

Chemical Composition Limits

Weight %SiFeCuMnCrMgNi

Zn

Ti + ZrTi
H15 HE 150.50-0.900.50 max3.9-5.00.4-1.20.10 max0.2-0.80.10 max

0.25 max

0.20 max0.15 max

 

Aluminum Alloy H15 is available in Bar,  Sheet and Plate.


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High strength alloys with excellent machinability widely used in aircraft. Have limited formability and only fair corrosion resistant in the heat treated condition. Not recommended for fusion welding. Used for high strength parts in aircraft and machinery, including gears and bolts and for security vans where strength ids critical. It has a tendency to allow the removal of a greater volume of metal in a single operation for an equipment standard of finish than 6082. Durability, however, is lower and needs a protection coating. Machines better in solution treated condition than fully heat treated. Used for machined parts where these characteristics are critical.

Data Sheet:

Aluminium Alloy 24534

Chemical Composition Limits

Weight %SiFeCuMnCrMgOTHER 

 



245340.20-0.700.70 max3.5-4.70.4-1.20.10 max0.4-1.20.50 max

 



 

Aluminum Alloy 24534 is available in Bar, Sheet and Plate.


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High strength alloys with excellent machinability widely used in aircraft. Have limited formability and only fair corrosion resistant in the heat treated condition. Not recommended for fusion welding. Used for high strength parts in aircraft and machinery, including gears and bolts and for security vans where strength ids critical. It has a tendency to allow the removal of a greater volume of metal in a single operation for an equipment standard of finish than 6082. Durability, however, is lower and needs a protection coating. Machines better in solution treated condition than fully heat treated. Used for machined parts where these characteristics are critical.

Data Sheet:

Aluminium Alloy HE 14

Chemical Composition Limits

Weight %SiFeCuMnCrMgOTHER

 



HE 140.20-0.700.70 max3.5-4.70.4-1.20.10 max0.4-1.20.50 max

 



 

Aluminum Alloy HE 14 is available in Bar, Sheet and Plate.


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7075 Aluminum Alloy Plate and Sheet

Description 
Alloy 7075 has been the standard workhorse 7XXX series alloy within the aerospace industry ever since. It was the first successful Al-Zn-Mg-Cu high strength alloy using the beneficial effects of the alloying addition of chromium to develop good stress-corrosion cracking resistance in sheet products. Although other 7XXX alloys have since been developed with improved specific properties, alloy 7075 remains the baseline with a good balance of properties required for aerospace applications.

Alloy 7075 is available in bare and alclad sheet and plate product forms in the annealed state as well as several tempers of the T6, T73 and T76 types.

Applications 
Alloy 7075 sheet and plate products have application throughout aircraft and aerospace structures where a combination of high strength with moderate toughness and corrosion resistance are required.

Typical applications are alclad skin sheet, structural plate components up to 4 inches in thickness and general aluminum aerospace applications.

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We are able to supply Aluminum Plate 6063 with the vast support of our team.

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We have been able to offer our clients a qualitative range of Aluminum Sheet 19000.

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Product Details:
Minimum Order Quantity10 Kilogram
Weight10kg/ingot

LM25 Aluminium Casting Alloy (Al – Si7Mg)

This alloy conforms to British Standard 1490 LM25. Castings are standardised in the following conditions - as cast, LM25-M precipitation treated LM25 - TE; solution treated and stabilized LM25 - TB7; and fully heat - treated LM25 - TF.

CHEMICAL COMPOSITION

Copper 0.1 max.
Magnesium 0.20-0.60
Silicon 6.5-7.5
Iron 0.5 max.
Manganese 0.3 max.
Nickel 0.1 max.
Zinc 0.1 max.
Lead 0.1 max.
Tin 0.05 max.
Titanium* 0.2 max.
Aluminium Remainder.

* 0.05% min. if Titanium alone used for grain refining.

STRENGTH AT ELEVATED TEMPERATURES The tensile properties of LM25 alloy at elevated temperatures are influenced by the condition (heat -treatment) of the castings and the duration at the elevated temperature. For short term testing e.g. 30 minutes at temperature, the properties fall only slowly and uniformly up to about 200oC at which temperature for example, the strength of LM25-TF is reduced by approximately 20%, Very prolonged heating (10,000 hours) results in sharp, loss of strength at about135oC and at 200oC the strength on LM25-TS is less than half of that at room temperature. For prolonged service at elevated temperatures (above 130oC) there is, therefore, no practical advantage to be gained by heat treatment.

PHYSICAL PROPERTIES
Coefficient of Thermal Expansion (per oC at 20 -100 oC) 0.000022
Thermal Conductivity (cal/cm2/cm/oC/s at 25oC * 0.36
Electrical Conductivity (% copper standard at 20oC) * 39
Specific Gravity 2.68
Freezing Range (oC) Approx 615-550
*Applies to fully heat treated sand castings; values are approximate and for castings in other conditions will depend on their thermal history.

MACHINABILITY The heat treated alloy has fairly good machining properties, but tools should preferably be of high speed steel and must be kept sharp. A moderately high rate of tool wear may be expected. Liberal cutting lubricant should be employed. CORROSION RESISTANCE Resistance to corrosive attack by sea water and marine atmospheres is high. ANODISING A protective anodic film can be obtained by either the sulphuric or chromic acid process but the grey opaque character of coatings of normal thickness precludes their colouring in light shades for decorative purposes. CASTING

CHARACTERISTICS FLUIDITY Good, suitable for fairly thin castings. PRESSURE TEST Suitable for castings required to be leak tight. HOT TEARING The production of castings in this alloy very rarely introduces problems due to hot tearing.

TYPICAL POURING TEMPERATURE-710oC The actual temperatures employed may range considerably above or below this value and will depend upon the particular conditions for each castings.

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Mr. Pravin Jain  (Proprietor)
278, Ganesh Peth Laxmi Road
Rasta Peth, Pune - 411002 , Maharashtra , India
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