1. Product Overview

Inconel 792 is a precipitation-hardened, investment-cast nickel-based superalloy developed for demanding high-temperature applications in gas turbines and aero-engine hot sections.

The alloy is strengthened primarily by a high volume fraction ofγ′ (gamma-prime) precipitates, providing excellent high-temperature strength, creep resistance, stress-rupture resistance, and thermal-fatigue capability.

Chromium and aluminum contribute to oxidation and hot-corrosion resistance, while cobalt, molybdenum, tungsten, and tantalum contribute to solid-solution and precipitation strengthening, creep resistance, and high-temperature structural stability.

Inconel 792 is particularly suitable forprecision investment casting of complex and thin-wall components, followed by CNC machining to achieve the required dimensional and surface specifications.

Typical applications include:

· Turbine blades

· Nozzle guide vanes (NGVs)

· Blade platforms

· Tip shrouds

· Sealing components

· Combustion and hot-gas-path hardware

2. Material Classification

Item	Description
UNS Number	N07792
Material Type	Nickel-based precipitation-hardened superalloy
Manufacturing Process	Vacuum induction melting+casting
Primary Strengthening Mechanism	γ′ precipitation strengthening
Typical Supply Condition	Solution-treated and age-hardened
Primary Service Environment	High-temperature gas-turbine and aerospace hot sections

3. Supply Condition

Inconel 792 is typically supplied in aninvestment-cast, solution-treated, and age-hardened condition.

The final heat-treatment condition may be selected according to casting process, component geometry, required mechanical properties, and applicable customer or OEM specifications.

A representative heat-treatment practice reported for IN-792 is:

·Solution treatment:approximately 1120 °C / 2 h / air cool

·Aging treatment:approximately 840 °C / 24 h / air cool

Actual heat-treatment parameters shall be confirmed against the applicable material specification and production qualification requirements.

4. Chemical Composition

Table 1 — Typical Chemical Composition

Element	Typical / Specified Range (wt.%)	Primary Function
Nickel (Ni)	Balance	Matrix element; high-temperature strength
Chromium (Cr)	12.0–16.0	Oxidation and hot-corrosion resistance
Cobalt (Co)	8.5–9.5	Solid-solution strengthening and thermal-fatigue stability
Aluminum (Al)	3.15–3.60	γ′ formation and precipitation strengthening
Titanium (Ti)	3.75–4.20	γ′ strengthening and high-temperature strength
Molybdenum (Mo)	1.65–2.10	Solid-solution strengthening and creep resistance
Tungsten (W)	3.85–4.50	Solid-solution strengthening and creep resistance
Tantalum (Ta)	3.85–4.50	γ′ strengthening, carbide formation and creep resistance
Carbon (C)	0.06–0.10	Grain-boundary carbide formation
Boron (B)	0.01–0.02	Grain-boundary strengthening and ductility
Zirconium (Zr)	0.01–0.05	Grain-boundary stability and toughness
Silicon (Si)	≤0.10	Casting and oxidation behavior
Manganese (Mn)	≤0.10	Melting and casting-process control

Note:Chemical composition values should be verified against the applicable alloy specification, heat certificate, or approved supplier specification before being used as guaranteed material limits.

5. Physical Properties

Table 2 — Typical Physical Properties

Property	Typical Value	Test Method / Condition
Density	8.25 g/cm³	Typical literature value
Melting Range	1260–1335 °C	Manufacturer / supplier typical data
Thermal Conductivity	10.9 W/m·K (100 °C)	ASTM E1225
Electrical Resistivity	1.32 µΩ·m (20 °C)	ASTM B193
Coefficient of Thermal Expansion	Temperature dependent	ASTM E228
Specific Heat	445 J/kg·Kat room temperature	ASTM E1269
Elastic Modulus	~185 GPa at room temperature	ASTM E111

Note:Physical properties vary with temperature, heat-treatment condition, casting process, and microstructure. Temperature-dependent engineering data should be established from validated material testing when required for design.

6. Mechanical Properties

Table 3 — Typical Mechanical Properties

Investment-Cast, Heat-Treated Condition

Property	Typical Value	Test Standard / Condition
Ultimate Tensile Strength	typically ~880–1200 MPa	ASTM E8/E8M
0.2% Yield Strength	typically ~800–1000 MPa	ASTM E8/E8M
Elongation	Typically ~3–6%	ASTM E8/E8M
Hardness	Condition dependent; typically ~330–400 HB	ASTM E10

Mechanical properties depend strongly on casting quality, heat-treatment condition, grain structure, specimen orientation, section thickness, and test temperature. Values should therefore be treated as typical engineering data unless explicitly specified as guaranteed minimum requirements.

7. Creep and Stress-Rupture Properties

Table 4 — Creep / Stress-Rupture Performance

Test Temperature	Applied Stress	RuptureLife	Elongation
750 °C	564 MPa	30 h	≥5%
950 °C	217 MPa	30 h	≥2%

These values represent the specified creep/stress-rupture performance under the stated test conditions.

Test method:ASTM E139 or applicable customer/OEM specification.

For design applications, creep and stress-rupture allowables should be established using material-specific qualification data covering the required temperature, stress level, exposure time, casting condition, heat treatment, and component geometry.

8. Key Material Characteristics

8.1 High γ′ Precipitation Strengthening

The high volume fraction of γ′ precipitates provides strong precipitation strengthening and contributes to the retention of mechanical properties during prolonged high-temperature exposure.

8.2 Creep and Stress-Rupture Resistance

The combination of γ′ strengthening and refractory alloying elements contributes to resistance against creep deformation and stress rupture under elevated-temperature loading.

8.3 Oxidation and Hot-Corrosion Resistance

Chromium and aluminum promote protective oxide formation, providing resistance to oxidation and hot-corrosion environments encountered in gas-turbine and combustion systems.

8.4 Thermal-Fatigue Resistance

The alloy is suitable for components subjected to repeated thermal cycling and thermo-mechanical loading in high-temperature service.

8.5 Investment-Casting Capability

Inconel 792 is suitable for precision investment casting of complex geometries, including thin-wall airfoils, platforms, shrouds, and nozzle guide vanes.

9. CNC Machining Characteristics

Inconel 792 presents machining challenges typical of precipitation-strengthened nickel-based superalloys.

Table 5 — CNC Machining Challenges and Recommended Approaches

Challenge	Description	Recommended Approach
High hardness and γ′ strengthening	High cutting forces and accelerated tool wear	Use rigid tooling and wear-resistant cutting tools
Low thermal conductivity	Heat concentrates in the cutting zone	Apply effective coolant delivery and optimized cutting parameters
Work hardening	Repeated tool engagement can produce a hardened surface layer	Avoid tool dwelling and rubbing; maintain consistent cutting engagement
Carbide and hard second phases	Can contribute to abrasive and mechanical tool wear	Select appropriate tool grade and cutting-edge geometry
Tool-edge chipping	High cutting forces and interrupted cuts can destabilize the cutting edge	Use suitable edge strength and controlled tool engagement
Chip control	Tough chips may interfere with machining and surface quality	Use appropriate chipbreaker geometry and controlled cutting conditions
Thin-wall deformation	Complex airfoils and thin sections may be susceptible to vibration and distortion	Use rigid workholding and optimized multi-axis tool paths

Recommended CNC Practices

· Use sharp, wear-resistant tooling suitable for nickel-based superalloys.

· Maintain consistent cutting engagement.

· Avoid prolonged tool dwelling.

· Apply effective coolant directly to the cutting zone.

· Use rigid fixturing and stable machining strategies.

· Minimize unnecessary radial engagement.

· Monitor tool wear closely when machining thin-wall airfoils and precision sealing surfaces.

· Establish final cutting parameters through controlled process trials.

10. Dimensional and Surface-Finish Capability

Precision CNC machining can achieve tight dimensional tolerances and fine surface finishes when appropriate tooling, fixturing, machining parameters, and inspection methods are applied.

Typical achievable tolerance and surface finish depend on:

· Component geometry

· Wall thickness

· Machine-tool capability

· Tooling system

· Workholding

· Cutting parameters

· Tool wear

· Coolant strategy

· Inspection method

Therefore, dimensional tolerance and surface roughness should be specified on the individual component drawing or manufacturing specification rather than treated as intrinsic material properties.

11. Typical Applications

11.1 Aero-Engine and Gas-Turbine Applications

Typical applications include:

· Turbine blades

· Nozzle guide vanes (NGVs)

· Blade platforms

· Tip shrouds

· Sealing components

· Selected hot-section structural components

The alloy provides a combination of high-temperature strength, creep resistance, oxidation resistance, and thermal-fatigue capability.

11.2 Power Generation

Potential applications include:

· Gas-turbine stator components

· Hot-gas-path hardware

· Combustion-system components

· Nozzle and vane assemblies

· Stationary high-temperature components

The alloy is suitable for applications involving prolonged exposure to elevated temperatures and cyclic thermal loading.

11.3 Aerospace and Defense

Potential applications include:

· Aero-engine hot-section components

· High-temperature structural hardware

· Hot-gas-path components

· Nozzle and duct components

The combination of high-temperature mechanical strength, oxidation resistance, and thermal-fatigue capability makes the alloy suitable for demanding aerospace propulsion environments.

11.4 Energy and Industrial Gas Turbines

Potential applications include:

· Stationary turbine components

· Blade platforms

· Turbine vanes

· Hot-gas-path components

· High-temperature structural hardware

The material is particularly suitable where long-term dimensional stability and resistance to creep deformation are required.

12. Manufacturing and Quality Considerations

For investment-cast Inconel 792 components, final performance depends on more than nominal alloy chemistry. Important factors include:

·Vacuum induction melting

· Casting quality

· Grain structure

· Heat-treatment condition

· Internal porosity

· Non-metallic inclusions

· Residual stress

· Surface condition

· Machining integrity

For critical aerospace and power-generation components, quality-control programs may include:

· Chemical composition verification

· Heat-treatment traceability

· Dimensional inspection

· Hardness testing

· Tensile testing

· Radiographic / X-ray inspection

· Fluorescent penetrant inspection

· Metallographic examination

· Creep or stress-rupture testing where required

Acceptance criteria should be defined according to the applicable customer drawing, purchasing specification, OEM requirement, or governing material specification.

13. Material Summary

Category	Inconel 792
Material	Inconel 792
UNS	N07792
Material Class	Nickel-based precipitation-hardened superalloy
Manufacturing Route	Precision investment casting
Strengthening Mechanism	γ′ precipitation strengthening
Typical Supply Condition	Solution-treated + age-hardened
Density	~8.25 g/cm³
Tensile Strength	~880–1020 MPa, condition dependent
Elongation	~3–6%, condition dependent
Hardness	~330–400 HB, condition dependent
Stress-Rupture @ 750 °C	564 MPa / 30 h / EL ≥5%
Stress-Rupture @ 950 °C	217 MPa / 30 h / EL ≥2%
Main Advantages	High-temperature strength · Creep resistance · Stress-rupture resistance · Oxidation resistance · Thermal-fatigue resistance
Main Applications	Turbine blades · NGVs · Platforms · Shrouds · Hot-gas-path components

14. Product Capability

Manufacturing:Vacuum induction melting &Casting
Heat Treatment:Solution Treatment + Aging
Inspection:Dimensional Inspection / NDT / Metallography / Mechanical Testing
Applications:Aerospace · Gas Turbine · Power Generation · Energy