turbine blades

Manufacturing Processes for Engineering Materials, 5th ed. Kalpakjian • Schmid© 2008, Pearson EducationISBN No. 0-13-227271-7

Turbine Blades


FIGURE 3.1 Turbine blades for jet engines, manufactured by three different methods: (a) conventionally cast; (b) directionally solidified, with columnar grains, as can be seen from the vertical streaks; and (c) single crystal. Although more expensive, single-crystal blades have properties at high temperatures that are superior to those of other blades. Source: Courtesy of United Technologies Pratt and Whitney.

(a) (b) (c)


Common Crystal Structures

FIGURE 3.2 The body-centered cubic (bcc) crystal structure: (a) hard-ball model; (b) unit cell; and (c) single crystal with many unit cells. Common bcc metals include chromium, titanium, and tungsten. Source: After W.G. Moffatt.

(a) (b) (c)

a

a

a

a

a

R

(a) (b) (c)

a

a

aa

a

2R

(a) (b)

aa

c

FIGURE 3.3 The face-centered cubic (fcc) crystal structure: (a) hard-ball model; (b) unit cell; and (c) single crystal with many unit cells. Common fcc metals include aluminum, copper, gold and silver.Source: After W.G. Moffatt.

FIGURE 3.4 The hexagonal close-packed (hcp) crystal structure: (a) unit cell; and (b) single crystal with many unit cells. Common hcp metals include zinc, magnesium and cobalt. Source: After W.G. Moffatt.


Plastic Deformation in Crystals

FIGURE 3.5 Permanent deformation of a single crystal under a tensile load. The highlighted grid of atoms emphasizes the motion that occurs within the lattice.(a) Deformation by slip. The b/a ratio influences the magnitude of the shear stress required to cause slip. Note that the slip planes tend to align themselves in the direction of pulling. (b) Deformation by twinning, involving generation of a “twin” around a line of symmetry subjected to shear. Note that the tensile load results in a shear stress in the plane illustrated.

(a) (b)

Shear stress

Slip plane

ab

Shearstress

Twinningplane

Atomicplanes


Shear Stress at Atomic Scale

FIGURE 3.6 Variation of shear stress in moving a plane of atoms over another plane.

max

a

b

x

1 2 3 4 5

τ= τmax sin2πxb

τmax =G2π

Shear stress:

Leads to:


Slib Bands in a Single Crystal

FIGURE 3.7 Schematic illustration of slip lines and slip bands in a single crystal subjected to a shear stress. A slip band consists of a number of slip planes. The crystal at the center of the upper drawing is an individual grain surrounded by other grains.

~10,000 atomic

diameters

stre

ss

Shear

Slip band

Slip lines approximately100 atomicdiameters

Single crystal(grain)

Grainboundaries

Approximately 1000atomic diameters


Normal Stress in a Single Crystal

FIGURE 3.8 Variation of cohesive stress as a function of distance between a row of atoms.

a

x

Tensile

stress

Distance

between atoms

!max

"2

!

!

Work=σmaxλπ

σmax =!Eγa≈ E10

Work:

Leads to:


Crystal Defects

FIGURE 3.9 Various defects in a single-crystal lattice. Source: After W.G. Moffatt.

Vacancy

Interstitialimpurity atom

Substitutionalimpurity atom

Self-interstitial atom

(b)(a)

ScrewdislocationFIGURE 3.10 (a) Edge dislocation, a linear

defect at the edge of an extra plane of atoms. (b) Screw dislocation, a helical defect in a three-dimensional lattice of atoms. Screw dislocations are so named because the atomic planes form a spiral ramp.


Movement of Edge Dislocation

FIGURE 3.11 Movement of an edge dislocation across the crystal lattice under a shear stress. Dislocations help explain why the actual strength of metals is much lower than that predicted by atomic theory.

Slip plane


Grains During Solidification

FIGURE 3.12 Schematic illustration of the various stages during solidification of molten metal. Each small square represents a unit cell. (a) Nucleation of crystals at random sites in the molten metal. Note that the crystallographic orientation of each site is different. (b) and (c) Growth of crystals as solidification continues. (d) Solidified metal, showing individual grains and grain boundaries. Note the different angles at which neighboring grains meet each other. Source: After W. Rosenhain.

(c) (b) (d) (a)


Tensile Stress in Polycrystalline Material

FIGURE 3.13 Variation of tensile stress across a plane of polycrystalline metal specimen subjected to tension. Note that the strength exhibited by each grain depends on its orientation.

Average stress

Str

ess

Tensile stress


Grain Sizes

TABLE 3.1 Grain sizes.ASTM No. -3 0 3 5 7 9 12Grains/mm2 1 8 64 256 1,024 4,096 32,800Grains/mm3 0.7 16 360 2,900 23,000 185,000 4,200,000

ASTM Grain Size Number:

Hall-Petch Equation:

N = 2n!1

Y = Yi+ kd!1/2


Embrittlement & Plastic Deformation

FIGURE 3.14 Embrittlement of copper by lead and bismuth at 350°C (660°F). Embrittlement has important effects on the strength, ductility, and toughness of materials. Source: After W. Rostoker.

Strain

100% Bi

Wetting agent100% Pb

20% Pb-80% Bi

80% Pb-20% Bi

Unwetted

Str

ess

FIGURE 3.15 Plastic deformation of idealized (equiaxed) grains in a specimen subjected to compression, such as is done in rolling or forging of metals: (a) before deformation; and (b) after deformation. Note the alignment of grain boundaries along a horizontal direction.

(b)(a)


Crack Due to Bulging

FIGURE 3.16 (a) Illustration of a crack in sheet metal subjected to bulging, such as by pushing a steel ball against the sheet. Note the orientation of the crack with respect to the rolling direction of the sheet. This material is anisotropic. (b) Aluminum sheet with a crack (vertical dark line at the center) developed in a bulge test. Source: Courtesy of J.S. Kallend, Illinois Institute of Technology.

(a)

Side view

Top view

Crack

Sheet

Rollingdirection

(b)


Recovery, Recrystallization and Grain Growth

FIGURE 3.17 Schematic illustration of the effects of recovery, recrystallization, and grain growth on mechanical properties and shape and size of grains. Note the formation of small new grains during recrystallization. Source: After G. Sachs.

StrengthDuctility

Hardness

Cold-workedand recovered New grains

Temperature

Recrystal-lization

Recovery Graingrowth

Grainsize

Residualstresses

Strength,hardness,ductility


Recrystallization

FIGURE 3.19 The effect of prior cold work on the recrystallized grain size of alpha brass. Below a critical elongation (strain), typically 5%, no recrystallization occurs.

Increasingtemperature

Str

ength

and h

ard

ness

Constant reduction

Time

Str

ength

and h

ard

ness

Increasingreduction

Constant temperature

Time

(a) (b)

FIGURE 3.18 Variation of strength and hardness with recrystallization temperature, time, and prior cold work. Note that the more a metal is cold worked, the less time it takes to recrystallize, because of the higher stored energy from cold working due to increased dislocation density.

0.4

0.3

0.2

0.1

00 10 20 30 40

Recry

sta

llized g

rain

siz

e (

mm

)

Elongation (%)


Surface Roughness; Homologous Temperature

FIGURE 3.20 Surface roughness on the cylindrical surface of an aluminum specimen subjected to compression. Source: A. Mulc and S. Kalpakjian.

TABLE 3.2 Homologous Temperature Ranges for Various Processes.

Process T/Tm

Cold working < 0.3Warm working 0.3 to 0.5Hot working > 0.6


Failure

FIGURE 3.22 Schematic illustration of the types of fracture in tension: (a) brittle fracture in polycrystalline metals; (b) shear fracture in ductile single crystals (see also Fig. 3.5a); (c) ductile cup-and-cone fracture in polycrystalline metals (see also Fig. 2.2); (d) complete ductile fracture in polycrystalline metals, with 100% reduction of area.

Barreling

Cracks

(a) (b) (c) (d)

FIGURE 3.21 Schematic illustration of types of failure in materials: (a) necking and fracture of ductile materials; (b) buckling of ductile materials under a compressive load; (c) fracture of brittle materials in compression; (d) cracking on the barreled surface of ductile materials in compression. (See also Fig. 6.1b)

(a) (b) (c) (d)


Ductile Fracture Surface

FIGURE 3.23 Surface of ductile fracture in low-carbon steel, showing dimples. Fracture is usually initiated at impurities, inclusions, or preexisting voids in the metal. Source: K.-H. Habig and D. Klaffke. Photo courtesy of BAM, Berlin, Germany.


Sequence in Necking and Fracture

FIGURE 3.24 Sequence of events in necking and fracture of a tensile-test specimen: (a) early stage of necking; (b) small voids begin to form within the necked region; (c) voids coalesce, producing an internal crack; (d) rest of cross-section begins to fail at the periphery by shearing; (e) final fracture surfaces, known as cup-(top fracture surface) and-cone (bottom surface) fracture.

Shear Fibrous

(a) (b) (c) (d) (e)


Effect of Inclusions

FIGURE 3.25 Schematic illustration of the deformation of soft and hard inclusions and their effect on void formation in plastic deformation. Note that hard inclusions, because they do not comply with the overall deformation of the ductile matrix, can cause voids.

(a) Before deformation (b) After deformation

Matrix

Inclusion

Soft inclusion Hard inclusion

Void Strong direction

of deformed metalHard inclusion

Voids

or Weak direction


Transition Temperature & Strain Aging

FIGURE 3.26 Schematic illustration of transition temperature. Note the narrow temperature range across which the behavior of the metal undergoes a major transition.

Transitiontemperature

Du

ctilit

y, t

ou

gh

ne

ss

Temperature

FIGURE 3.27 Strain aging and its effect on the shape of the true-stress-true-strain curve for 0.03% C rimmed steel at 60°C (140°F). Source: A.S. Keh and W.C. Leslie.

350

300

250

200

150

100

Tru

e s

tre

ss (

MP

a)

0 0.02 0.04 0.06 0.08 0.10 0.12 0.14

50

40

30

20

psi x 1

03

True strain, !

126 hr

4 hr

30 min15 min

i

g

ch

f

eb

a d


Brittle and Intergranular Fracture

FIGURE 3.29 Intergranular fracture, at two different magnifications. Grains and grain boundaries are clearly visible in this micrograph. The fracture path is along the grain boundaries. Source: Courtesy of Packer Engineering.

FIGURE 3.28 Typical fracture surface of steel that has failed in a brittle manner. The fracture path is transgranular (through the grains). Compare this surface with the ductile fracture surface shown in Fig. 3.23. Source: Courtesy of Packer Engineering.


Fracture Mode & Surface

FIGURE 3.30 Three modes of fracture. Mode I has been studied extensively, because it is the most commonly observed in engineering structures and components. Mode II is rare. Mode III is the tearing process; examples include opening a pop-top can, tearing a piece of paper, and cutting materials with a pair of scissors.

Mode I

Mode IIMode III

FIGURE 3.31 Typical fatigue fracture surface on metals, showing beach marks. Most components in machines and engines fail by fatigue and not by excessive static loading. Source: Courtesy of Packer Engineering.


Fatigue

FIGURE 3.32 Reduction in fatigue strength of cast steels subjected to various surface-finishing operations. (a) Effect of surface roughness. Note that the reduction is greater as the surface roughness and strength of the steel increase. Source: After J.E. Shigley and L.D. Mitchell. (b) Effect of residual stress, as developed by shot peening (see Section 4.5.1). Source: After B.J. Hamrock, S.R. Schmid and B.O. Jacobson.

483

414

345

276

207

138

70

60

50

40

30

20

Str

ess a

mp

litu

de

, S

(MP

a)

ksi

104 105 106 107 108

Number of cycles to failure, N

Al 7050-T7651Ti-6Al-4V

Polished

(b)

Shot peened

Machined

(a)

Re

du

ctio

n in

fa

tig

ue

str

en

gth

(%

)

Ultimate tensile strength (psi x 103)

100 15050 200

500 800 1000 1300

MPa

Fine polishing

PolishingGrindingFine turning

Rough turning

As cast

60

70

50

40

30

20

10

0


Physical Properties of MaterialsCoe!cient

Thermal of ThermalDensity Melting Point Specific Heat Conductivity Expansion(kg/m3) (!C) (J/kg K) (W/m K) (µm/m!C)

METALAluminum 2700 660 900 222 23.6Aluminum alloys 2630-2820 476-654 880-920 121-239 23.0-23.6Beryllium 1854 1278 1884 146 8.5Columbium (niobium) 8580 2468 272 52 7.1Copper 8970 1082 385 393 16.5Copper alloys 7470-8940 885-1260 337-435 29-234 16.5-20Gold 19300 1063 129 317 19.3Iron 7860 1537 460 74 11.5Steels 6920-9130 1371-1532 448-502 15-52 11.7-17.3Lead 11,350 327 130 35 29.4Lead alloys 8850-11,350 182-326 126-188 24-46 27.1-31.1Magnesium 1745 650 1025 154 26.0Magnesium alloys 1770-1780 610-621 1046 75-138 26.0Molybdenum alloys 10,210 2610 276 142 5.1Nickel 8910 1453 440 92 13.3Nickel alloys 7750-8850 1110-1454 381-544 12-63 12.7-18.4Silicon 2330 1423 712 148 7.63Silver 10,500 961 235 429 19.3Tantalum alloys 16,600 2996 142 54 6.5Titanium 4510 1668 519 17 8.35Titanium alloys 4430-4700 1549-1649 502-544 8-12 8.1-9.5Tungsten 19,290 3410 138 166 4.5NONMETALLICCeramics 2300-5500 — 750-950 10-17 5.5-13.5Glasses 2400-2700 580-1540 500-850 0.6-1.7 4.6-70Graphite 1900-2200 — 840 5-10 7.86Plastics 900-2000 110-330 1000-2000 0.1-0.4 72-200Wood 400-700 — 2400-2800 0.1-0.4 2-60

TABLE 3.3 Physical Properties of Various Materials at Room Temperature.


Effect of Carbon on Steel Properties

FIGURE 3.33 Effect of carbon content on the mechanical properties of carbon steel.

Tensile strength

Yield strength

1000

800

600

400

200

Impactenergy

% elongation

0

Yie

ld a

nd tensile

str

ength

(M

Pa)

0 0.2 0.4 0.6 0.8 1.0

Carbon (%)

Elo

ngation (

%)

0

20

40

60

80

100

Izod im

pact energ

y (

Nm

)

140

120

100

80

60

40

NormalizedAnnealed

Lowcarbon

Mediumcarbon

Highcarbon


Annealed Stainless SteelsUltimateTensile Yield

AISI Strength Strength Elongation Characteristics and Typical(UNS) (MPa) (MPa) (%) Applications303(S30300)

550-620 240-260 50-53 Screw-machine products, shafts, valves, bolts,bushings, and nuts; aircraft fittings; rivets;screws; studs.

304(S30400)

565-620 240-290 55-60 Chemical and food-processing equipment, brew-ing equipment, cryogenic vessels, gutters, down-spouts, and flashings.

316(S31600)

550-590 210-290 55-60 High corrosion resistance and high creep strength.Chemical and pulp-handling equipment, photo-graphic equipment, brandy vats, fertilizer parts,ketchup-cooking kettles, and yeast tubs.

410(S41000)

480-520 240-310 25-35 Machine parts, pump shafts, bolts, bushings, coalchutes, cutlery, fishing tackle, hardware, jet en-gine parts, mining machinery, rifle barrels, screws,and valves.

416(S41600)

480-520 275 20-30 Aircraft fittings, bolts, nuts, fire extinguisher in-serts, rivets, and screws.

TABLE 3.4 Room-Temperature Mechanical Properties and Typical Applications of Annealed Stainless


Tool & Die Materials

TABLE 3.5 Basic Types of Tool and Die Steels.

Type AISIHigh speed M (molybdenum base)

T (tungsten base)Hot work H1 to H19 (chromium base)

H20 to H39 (tungsten base)H40 to H59 (molybdenum base)

Cold work D (high carbon, high chromium)A (medium alloy, air hardening)O (oil hardening)

Shock resisting SMold steels P1 to P19 (low carbon)

P20 to P39 (others)Special purpose L (low alloy)

F (carbon-tungsten)Water hardening W

Process MaterialDie casting H13, P20Powder metallurgy

Punches A2, S7, D2, D3, M2Dies WC, D2, M2

Molds for plastic and rubber S1, O1, A2, D2, 6F5, 6F6, P6, P20, P21, H13Hot forging 6F2, 6G, H11, H12Hot extrusion H11, H12, H13Cold heading W1, W2, M1, M2, D2, WCCold extrusion

Punches A2, D2, M2, M4Dies O1, W1, A2, D2

Coining 52100, W1, O1, A2, D2, D3, D4, H11, H12, H13Drawing

Wire WC, diamondShapes WC, D2, M2Bar and tubing WC, W1, D2

RollsRolling Cast iron, cast steel, forged steel, WCThread rolling A2, D2, M2Shear spinning A2, D2, D3

Sheet metalsShearing

Cold D2, A2, A9, S2, S5, S7Hot H11, H12, H13

Pressworking Zinc alloys, 4140 steel, cast iron, epoxy composites, A2, D2, O1Deep drawing W1, O1, cast iron, A2, D2Machining Carbides, high-speed steels, ceramics, diamond, cubic boron nitride

TABLE 3.5 Typical Tool and Die Materials for Various Processes.


Non-Ferrous Alloys in Aircraft Engine

FIGURE 3.34 Cross-section of a jet engine (PW2037) showing various components and the alloys used in making them. Source: Courtesy of United Aircraft Pratt & Whitney.

Ti alloy fanTi or Al alloy

low-pressure compressor

Ti or Ni alloyhigh-pressurecompressor

Ni alloyhigh-pressure

turbine

Ni alloylow-pressure

turbine

Turbineexhaust case

Ni alloy

TurbinebladesNi alloy

Accessory sectionAl alloy or Fe alloy

Inlet case Al alloy

Ni alloycombustion

chamber


Aluminum AlloysUltimate Tensile Yield Strength Elongation

Alloy (UNS) Temper Strength (MPa) (MPa) in 50 mm (%)1100 (A91100) O 90 35 35-451100 H14 125 120 9-201350 (A91350) O 85 30 231350 H19 185 165 1.52024 (A92024) O 190 75 20-222024 T4 470 325 19-203003 (A93003) O 110 40 30-403003 H14 150 145 8-165052 (A95052) O 190 90 25-305052 H34 260 215 10-146061 (A96061) O 125 55 25-306061 T6 310 275 12-177075 (A97075) O 230 105 16-177075 T6 570 500 118090 T8X 480 400 4-5

TABLE 3.7 Properties of Various Aluminum Alloys at Room Temperature


Wrought Aluminum Alloys

Characteristics!

CorrosionAlloy Resistance Machinability Weldability Typical Applications1100 A D-C A Sheet-metal work, spun hollow parts, tin-

stock.2014 C C-B C-B Heavy-duty forgings, plate and extrusions for

aircraft structural components, wheels.3003 A D-C A Cooking utensils, chemical equipment, pres-

sure vessels, sheet-metal work, builders’ hard-ware, storage tanks.

5054 A D-C A Welded structures, pressure vessels, tube formarine uses.

6061 B D-C A Trucks, canoes, furniture, structural applica-tions.

7005 D B-D B Extruded structural members, large heat ex-changers, tennis racquets, softball bats.

8090 A-B B-D B Aircraft frames, helicopter structural compo-nents.

! From A (excellent) to D (poor).

TABLE 3.8 Manufacturing Properties and Typical Applications of Wrought Aluminum Alloys.


Magnesium Alloys

UltimateTensile Yield Elongation

Composition (%) Strength Strength in 50 mmAlloy Al Zn Mn Zr Condition (MPa) (MPa) (%) Typical FormsAZ31B 3.0 1.0 0.2 F 260 200 15 Extrusions

H24 290 220 15 Sheet and platesAZ80A 8.5 0.5 0.2 T5 380 380 7 Extrusions and forgingsHK31A! 0.7 H24 255 255 8 Sheet and platesZK60A 5.7 0.55 T5 365 365 11 Extrusions and forgings! HK31A also contains 3%Th.

TABLE 3.9 Properties and Typical Forms of Various Wrought Magnesium Alloys.


Copper & Brass

UltimateType and Nominal Tensile Yield ElongationUNS Composition Strength Strength in 50 mmNumber (%) (MPa) (MPa) (%) Typical ApplicationsOxygen-free 99.99 Cu 220-450 70-365 55-4 Bus bars, waveguides, hollow conductors,

electronic lead in wires, coaxial cables and tubes,(C10100) microwave tubes, rectifiers.

Red brass, 85.0 Cu 270-72 70-435 55-3 Weather stripping, conduit, sockets,(C23000) 15.0 Zn fasteners, fire extinguishers, condenser and

heat-exchanger tubing.Low Brass, 80.0 Cu 300-850 80-450 55-3 Battery caps, bellows, musical instruments,

(C24000) 20.0 Zn clock dials, flexible hose.Free-cutting 61.5 Cu, 340-470 125-310 53-18 Gears, pinions, automatic high-speed

brass 3.0 Pb, screw-machine parts(C36000) 35.5 Zn

Naval brass 60.0 Cu, 380-610 170-455 50-17 Aircraft turnbuckle barrels, balls, bolts,(C46400 to 39.25 Zn, marine hardware, valve stems, condenserC46700) 0.75 Sn plates.

TABLE 3.10 Properties and Typical Applications of Various Wrought Copper and Brasses.


Wrought Bronzes

UltimateType and Nominal Tensile Yield ElongationUNS Composition Strength Strength in 50 mmNumber (%) (MPa) (MPa) (%) Typical ApplicationsArchitectural 57.0 Cu, 415 140 30 Architectural extrusions, storefronts,

bronze 3.0 Pb, (as extruded) thresholds, trim, butts, hinges.(C38500) 40.0 ZnPhosphor 95.0 Cu, 325-960 130-550 64-2 Bellows, clutch disks, cotter pins,

bronze, 5% A 5.0 Sn, diaphragms, fasteners, wire brushes,(C51000) trace P chemical hardware, textile machinery.

Free-cutting 88.0 Cu, 300-520 130-435 50-15 Bearings, bushings, gears, pinions, shafts,phosphor 4.0 Pb, thrust washers, valve parts.bronze 4.0 Zn,(C54400) 4.0 Sn

Low-silicon 98.5 Cu, 275-655 100-475 55-11 Hydraulic pressure lines, bolts, marinebronze, B 1.5 Si hardware, electrical conduits, heat-(C65100) exchanger tubing.

Nickel- 65.0 Cu, 390-710 170-620 45-3 Rivets, screws, zippers, camera parts,silver, 65-18 17.0 Zn, base for silver plate, nameplates,(C74500) 18.0 Ni etching stock.

TABLE 3.11 Properties and Typical Applications of Various Wrought Bronzes.


Nickel Alloys

Principal UltimateAlloying Tensile Yield elongation

Alloy Elements Strength Strength in 50 mm(Condition) (%) (MPa) (MPa) (%) Typical ApplicationsNickel 200 None 380-550 100-275 60-40 Chemical- and food-processing

(annealed) industry, aerospace equipment,electronic parts.

Duranickel 301 4.4 Al, 1300 900 28 Springs, plastics-extrusion(age hardened) 0.6 Ti equipment, molds for glass.

Monel R-405 30 Cu 525 230 35 Screw-machine products, water-(hot rolled) meter parts.

Monel K-500 29 Cu, 1050 750 20 Pump shafts, valve stems, springs.(age hardened) 3Al

Inconel 600 15 Cr, 640 210 48 Gas-turbine parts, heat-treating(annealed) 8 Fe equipment, electronic parts,

nuclear reactors.Hastelloy C-4 16 Cr, 785 400 54 High-temperature stability,

(solution treated 15 Mo resistance to stress-corrosionand quenched) cracking.

TABLE 3.12 Properties and Typical Applications of Various Nickel Alloys (All Alloy Names are Trade Names).


Nickel-Base Superalloys

UltimateTensile Yield Elongation

Strength Strength in 50 mmAlloy Condition (MPa) (MPa) (%) Typical ApplicationsAstroloy Wrought 770 690 25 Forgings for high-temperature

applications.Hastelloy X Wrought 255 180 50 Jet-engine sheet parts.IN-100 Cast 885 695 6 Jet-engine blades and wheels.IN-102 Wrought 215 200 110 Superheater and jet-engine parts.Inconel 625 Wrought 285 275 125 Aircraft engines and structures,

chemical-processing equipment.Inconel 718 Wrought 340 330 88 Jet-engine and rocket parts.MAR-M 200 Cast 840 760 4 Jet-engine blades.MAR-M 432 Cast 730 605 8 Integrally cast turbine wheels.Rene 41 Wrought 620 550 19 Jet-engine parts.Udimet 700 Wrought 690 635 27 Jet-engine parts.Waspaloy Wrought 525 515 35 Jet-engine parts.

TABLE 3.13 Properties and Typical Applications of Various Nickel-Base Superalloys at 870°C (1600°F) (All Alloy Names Are Trade Names)


Titanium Alloys

UltimateNominal Tensile Yield Elon-Composi- Con- Temp Strength Strength gationtion (%) UNS dition (◦C) (MPa) (MPa) (%) Typical Applications99.5 Ti R50250 Annealed 25 330 240 30 Airframes; chemical, desalination,

300 150 95 32 and marine parts; plate-type heatexchangers.

5 Al, 2.5 Sn R54520 Annealed 25 860 810 16 Aircraft-engine compressor blades300 565 450 18 and ducting; steam-turbine blades.

6 Al, 4V R56400 Annealed 25 1000 925 14 Rocket motor cases; blades and300 725 650 14 disks for aircraft turbines and425 670 570 18 compressors; orthopedic550 530 430 35 implants; structural forgings;

Solution 25 1175 1100 10 fasteners.+ age 300 980 900 10

13 V, 11 Cr, R58010 Solution 25 1275 1210 8 High-strength fasteners; aerospace3Al + age 425 1100 830 12 components; honeycomb panels.

TABLE 3.14 Properties and Typical Applications of Wrought Titanium Alloys.

turbine blades

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