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OEM 6151 Aluminum Metal Parts For Airplane Engine Box Metal Aluminum Forging Part

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OEM 6151 Aluminum Metal Parts For Airplane Engine Box Metal Aluminum Forging Part

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Brand Name :JIMA
Model Number :ALP
Certification :ISO9001-2008,SGS,ROHS.
Place of Origin :CHINA
MOQ :1PCS
Price :Negotiations
Payment Terms :T/T, L/C
Supply Ability :10000 pcs /per month
Delivery Time :15~30days
Packaging Details :Standard Export Wooden Pallet
Application :Automotive/Railway/Aerospace
Name :OEM 6151 Forging Aluminum Parts For Airplane Engine Box/Auto Parts/Metal Forging Part/Aluminum Forging Part
Standard :JIS, DIN, BS, ASTM, SAE.
Alloy :6151
Surface treatment :Anodizing,Plating,Satin,Painting,Powder Coating,Anodized etc
Process :Forging/Forged
Mold :Can be Customized
Sample :Can be Customized
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OEM 6151 Forging Aluminum Parts For Airplane Engine Box/Auto Parts/Metal Forging Part/Aluminum Forging Part

Product Details

Material

Aluminum Alloy 6151

Process

Forging+CNC+Heat Treatment

Surface Treatment

Transparent, Color Anodized, Hard Anodizing, Powder Coating;
Sandblasting, Laser Carving, Silk Screening;
Nickel-Plated, Chrome, Galvanized, Silver/Gold Plating;
Black Oxide Coating, Polishing; etc...

Manufacture Ability

Depends on The Complexity Of Different Products And Quantities

Experience

Aluminum Machining Service for 12 Years

Packaging

Standard Export Wooden Pallets
Another Request According to Your Needs

MOQ

1pcs

Sample

Can Be Customized

Mold

Can Be Customized

Lead Time

Mold for 15-20 Days

Process for 15-20 Days

OEM

Can Be Customized

Chemical Composition of 6151

Alloy

Si

Fe

Cu

Mn

Mg

Cr

Zn

Ti

Others

Al

Each

Total

6151

0.5-1.2

0.10max

0.35max

0.20max

0.45-0.80

0.15-0.35

0.25max

0.15max

0.05max

0.15max

Rest

Technical Specifications of 6151-T6

Physical Properties

Original Value

Comments

Density

2.71 g/cc

AA; Typical

Mechanical Properties

Original Value

Comments

Hardness, Brinell

100

500 kg load with 10 mm ball

Hardness, Knoop

126

Converted from Brinell Hardness Number

Hardness, Rockwell A

41.3

Converted from Brinell Hardness Value

Hardness, Rockwell B

63

Converted from Brinell Hardness Value

Hardness, Vickers

112

Converted from Brinell Hardness Value

Tensile Strength, Ultimate

290 MPa

Rolled rings; Radial; T6 and T652

303 MPa

Die forgings; Axis parallel to grain flow

303 MPa

Die forgings; Axis not parallel to grain flow

303 MPa

Rolled rings; Tangential; T6 and T652

303 MPa

Rolled rings; Axial; T6 and T652

330 MPa

28.0 MPa
@Temperature 371 °C

34.0 MPa
@Temperature 316 °C

45.0 MPa
@Temperature 260 °C

95.0 MPa
@Temperature 204 °C

195 MPa
@Temperature 149 °C

295 MPa
@Temperature 100 °C

330 MPa
@Temperature 24.0 °C

340 MPa
@Temperature -28.0 °C

345 MPa
@Temperature -80.0 °C

395 MPa
@Temperature -196 °C

Tensile Strength, Yield

241 MPa

Rolled rings; Axial; T6 and T652

241 MPa

Rolled rings; Radial; T6 and T652

255 MPa

Die forgings; Axis parallel to grain flow

255 MPa

Die forgings; Axis not parallel to grain flow

255 MPa

Rolled rings; Tangential; T6 and T652

295 MPa

22.0 MPa
@Strain 0.200 %,
Temperature 371 °C

27.0 MPa
@Strain 0.200 %,
Temperature 316 °C

34.0 MPa
@Strain 0.200 %,
Temperature 260 °C

85.0 MPa
@Strain 0.200 %,
Temperature 204 °C

185 MPa
@Strain 0.200 %,
Temperature 149 °C

275 MPa
@Strain 0.200 %,
Temperature 100 °C

298 MPa
@Strain 0.200 %,
Temperature 24.0 °C

310 MPa
@Strain 0.200 %,
Temperature -28.0 °C

315 MPa
@Strain 0.200 %,
Temperature -80.0 °C

345 MPa
@Strain 0.200 %,
Temperature -196 °C

Elongation at Break

2.0 %

Rolled rings; Radial; T6 and T652

4.0 %

Rolled rings; Axial; T6 and T652

5.0 %

Rolled rings; Tangential; T6 and T652

6.0 %

Die forgings; Axis not parallel to grain flow

10 %

Die forgings; Axis parallel to grain flow

17 %
@Temperature -80.0 °C

17 %
@Temperature -28.0 °C

17 %
@Temperature 24.0 °C

17 %
@Temperature 100 °C

20 %
@Temperature -196 °C

20 %
@Temperature 149 °C

30 %
@Temperature 204 °C

35 %
@Temperature 371 °C

43 %
@Temperature 316 °C

50 %
@Temperature 260 °C

17 %
@Thickness 1.60 mm

In 5 cm

Modulus of Elasticity

69.0 GPa

Average of Tension and Compression. In Al alloys, the compressive modulus is typically 2% greater than the tensile modulus. Estimated from trends in similar Al alloys.

Poissons Ratio

0.33

Estimated from trends in similar Al alloys.

Fatigue Strength

85.0 MPa
@# of Cycles 5.00e+8

Shear Modulus

26.0 GPa

Estimated from similar Al alloys.

Shear Strength

220 MPa

Electrical Properties

Original Value

Comments

Electrical Resistivity

23.0 ohm-cir-mil/ft
@Temperature 20.0 °C

AA; Typical

Thermal Properties

Original Value

Comments

CTE, linear

12.9 µin/in-°F
@Temperature 20.0 - 100 °C

AA; Typical; average over range

21.8 µm/m-°C
@Temperature -50.0 - 20.0 °C

23.0 µm/m-°C
@Temperature 20.0 - 100 °C

24.1 µm/m-°C
@Temperature 20.0 - 200 °C

25.0 µm/m-°C
@Temperature 20.0 - 300 °C

Specific Heat Capacity

0.895 J/g-°C

Thermal Conductivity

1190 BTU-in/hr-ft²-°F

AA; Typical at 77°F

Melting Point

1090 - 1200 °F

AA; Typical range based on typical composition for wrought products >= 1/4 in. thickness. Eutectic melting can be eliminated by homogenization.

Solidus

1090 °F

AA; Typical

Liquidus

1200 °F

AA; Typical

Processing Properties

Original Value

Comments

Annealing Temperature

775 °F

hold at temperature 2 to 3 hr; furnace cool to 500°F at 50°F per hour max

Solution Temperature

950 - 975 °F

hold at temperature for 4 min, and quench in cold water; for heavy or complicated forgings, quench in water at 150 to 212°F

Aging Temperature

300 - 345 °F

hold at temperature 8 to 12 hr

Hot-Working Temperature

500 - 900 °F

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OEM 6151 Aluminum Metal Parts For Airplane Engine Box Metal Aluminum Forging Part

OEM 6151 Aluminum Metal Parts For Airplane Engine Box Metal Aluminum Forging Part

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