Inconel Forging Supplier for US Aeroengine and Gas Turbine Programmes

Knowledge Base

July 22, 2026

Inconel forgings for US aeroengine and gas turbine programmes represent the highest-value and most technically demanding segment of the global aerospace forging supply chain. A single Inconel 718 high-pressure compressor disc forging for a GE9X or Pratt & Whitney GTF engine may be worth $80,000–250,000 in the rough-forged condition. The complete Inconel forging content of a modern high-bypass turbofan engine compressor discs, turbine discs, shafts, seal rings, and structural components runs to several million dollars per engine. Indian forging manufacturers with demonstrated Inconel 718 and Inconel 625 production history, double-ageing heat treatment capability, AMS 2750-calibrated furnaces, immersion UT with nickel alloy calibration standards, and AS9100D certification are positioned to supply US aeroengine and gas turbine forging programmes at significant cost advantage over domestic US and European nickel alloy forging suppliers.

At a Glance: Inconel Forging Requirements for US Aeroengine Programmes

Component	Alloy	Condition	AMS Spec	Critical Process	US Buyers
HP compressor disc	Inconel 718	STA (double aged)	AMS 5663	Double ageing, delta phase, immersion UT	GE Aerospace, P&W
LP compressor disc	Inconel 718 / Ti-6Al-4V	STA	AMS 5663	Same as HP disc	GE, P&W, Rolls-Royce US
Turbine disc	Inconel 718 / Rene 88DT	STA	AMS 5663	Maximum temperature capability, UT	GE Aerospace
Engine shaft	Inconel 718	STA	AMS 5663	Immersion UT, straightness	GE, P&W
Seal rings	Inconel 718	STA	AMS 5663	Ring rolling, dimensional	All
Structural casing	Inconel 625	Annealed	AMS 5666	Solution anneal, UT	GE, P&W, Rolls-Royce US
Combustor liners (forgings)	Inconel 625	Annealed	AMS 5666	Solution anneal, FPI	GE, P&W
Industrial gas turbine	Inconel 718 / 625	STA / Annealed	AMS 5663/5666	AS9100D, heat treatment	GE Vernova, Siemens US

The US Aeroengine Forging Market: Who Buys Inconel Forgings

Commercial Aeroengines

GE Aerospace (formerly GE Aviation) — produces the GE9X (Boeing 777X), GEnx (Boeing 787), CF6, and CFM56/LEAP (joint venture with Safran through CFM International). GE Aerospace is headquartered in Evendale, Ohio, with manufacturing operations across Ohio, North Carolina, and internationally. Annual revenue exceeding $30 billion. Inconel forging consumption: thousands of disc and shaft forgings annually across all engine programmes.

Pratt & Whitney (RTX) — produces the PW1000G Geared Turbofan (GTF) family powering the Airbus A320neo, A220, Embraer E-Jets E2, and Mitsubishi SpaceJet; the F135 military engine for the F-35; and legacy engines including PW4000 and JT8D for the overhaul market. Headquartered in East Hartford, Connecticut. Inconel forging consumption: substantial across the GTF and F135 programmes.

Rolls-Royce North America — while primarily a UK company, Rolls-Royce has significant US operations including the Trent XWB (Airbus A350) and Trent 1000 (Boeing 787) support, and the LiftSystem for the F-35B vertical lift variant. US procurement teams source Inconel forgings for US-based maintenance, repair, and overhaul (MRO) of Rolls-Royce engines through US supply chain channels.

Honeywell Aerospace — produces auxiliary power units (APUs) and smaller aeroengines for business jets, regional aircraft, and military platforms. Inconel forging requirements include small-diameter disc and shaft forgings for APU turbomachinery.

Military Aeroengines

GE Aerospace — F414 and F110: The F414 turbofan powers the F/A-18E/F Super Hornet and the Boeing EA-18G Growler. The F110 turbofan powers the F-16 Fighting Falcon. Both engines use Inconel 718 compressor and turbine disc forgings.

Pratt & Whitney — F135 and F119: The F135 powers the F-35 Lightning II the largest military aeroengine programme in the world by production volume. The F119 powers the F-22 Raptor. Both use Inconel 718 for compressor and turbine rotating components.

GE Aerospace — T700: The T700 turboshaft powers the US Army’s UH-60 Black Hawk and AH-64 Apache helicopters. Inconel forging requirements for T700 include small-diameter compressor and turbine disc forgings and shaft forgings.

Industrial Gas Turbines

GE Vernova (formerly GE Power) — GE’s industrial gas turbine business (9HA, 7HA, LM2500, LM6000 series) uses Inconel 718 and Inconel 625 forgings for compressor disc and shaft components. Industrial gas turbines operate at lower rotational speeds than aeroengines but at higher firing temperatures and for much longer continuous operating periods. Inconel forging requirements for industrial gas turbines share many technical characteristics with aeroengine requirements but with longer service intervals and higher cyclic temperature exposure.

Siemens Energy US — Siemens Energy’s US gas turbine operations use Inconel forgings for the SGT-800, SGT-400, and larger frame machines. Siemens Energy North America sources forgings through US-based procurement and from international suppliers including India.

Inconel 718: The Dominant Alloy for US Aeroengine Forgings

Why Inconel 718 Dominates Aeroengine Rotating Components

Inconel 718 (UNS N07718) — a nickel-chromium-iron alloy with niobium, molybdenum, and titanium additions has been the standard material for aeroengine rotating components since the 1960s. Its combination of properties is uniquely suited to the high-stress, high-temperature cyclic loading environment of a gas turbine compressor or turbine disc:

Strength: Minimum 0.2% yield strength 1,030 MPa (150,000 psi) in the solution treated and aged (STA) condition. This is significantly higher than other common aerospace alloys at equivalent temperatures.

Temperature capability: Maintains adequate strength to approximately 650°C (1,200°F). Above this temperature, Inconel 718’s gamma double prime (γ″) precipitate strengthening mechanism becomes unstable. For turbine discs operating above 650°C, alternative alloys (Rene 88DT, ME3, LSHR) are used. For compressor discs and shafts operating below 650°C, Inconel 718 is the standard.

Fatigue resistance: Excellent high-cycle fatigue (HCF) and low-cycle fatigue (LCF) performance — critical for rotating components that experience thousands of pressure cycles per flight and millions of vibration cycles per hour of operation.

Oxidation resistance: Adequate resistance to the hot air environment in the compressor at operating temperatures below 650°C.

Weldability: Relatively good weldability compared to other nickel superalloys important for aeroengine assembly where disc forgings are welded to adjacent components in some designs.

Supply chain maturity: Extensive production history at recognised mills (Special Metals, Haynes International, ATI, Carpenter Technology) with well-established AMS 5663 certification processes and a large installed base of qualified forging manufacturers.

The AMS 5663 Specification

AMS 5663 — Nickel Alloy, Corrosion and Heat Resistant, Bars, Forgings, and Rings, 52.5Ni-19Cr-3.0Mo-5.1(Cb+Ta)-0.90Ti-0.50Al-18Fe, Consumable Electrode or Vacuum Induction Melted, Solution Heat Treated, Precipitation Heat Treated — is the primary material specification for Inconel 718 aerospace forgings.

Key AMS 5663 requirements:

Chemistry: Nickel 50–55%, Chromium 17–21%, Niobium+Tantalum 4.75–5.50%, Molybdenum 2.80–3.30%, Titanium 0.65–1.15%, Aluminium 0.20–0.80%, Iron balance. Chemistry is tightly controlled – niobium content directly determines the amount of gamma double prime precipitate achievable after ageing and therefore the maximum strength potential.

Melting practice: Vacuum induction melting (VIM) followed by either vacuum arc remelting (VAR) or electroslag remelting (ESR) — double melt process. The VIM step provides precise chemistry control; the VAR or ESR second melt refines the microstructure and removes segregation. Air-melted or single-melt Inconel 718 is not acceptable for aerospace rotating components.

Heat treatment: Solution anneal at 955°C ± 14°C, 1 hour, air cool or faster. Then age at 718°C ± 8°C, 8 hours, furnace cool at 55°C per hour maximum to 621°C ± 8°C, hold 8 hours total ageing time, air cool. This double-ageing sequence is mandatory — it develops both the primary gamma double prime (γ″) precipitate (at 718°C) and the secondary gamma prime (γ′) precipitate (at 621°C) that give Inconel 718 its high strength.

Tensile properties after STA:

Ultimate tensile strength: minimum 1,380 MPa (200,000 psi)
0.2% yield strength: minimum 1,030 MPa (150,000 psi)
Elongation: minimum 12%
Reduction of area: minimum 15%

The Double Ageing Heat Treatment: The Most Critical Process for US Buyers

Why the Double Age Is So Precisely Specified

The double ageing procedure for Inconel 718 is specified with temperature tolerances of ±8°C because the gamma double prime (γ″) precipitate size and distribution — which determines the alloy’s strength is extremely sensitive to ageing temperature and time.

If ageing temperature is too high (above 726°C): The γ″ precipitate grows too large (overaged condition) and the peak strength is not achieved. Additionally, at temperatures above 650°C, the metastable γ″ precipitate begins to transform to the stable delta phase (δ, Ni₃Nb orthorhombic) — which has no strengthening contribution and actually depletes the niobium available for γ″ formation.

If ageing temperature is too low (below 710°C): The γ″ precipitate forms but does not grow to its peak strengthening size – underaged condition. Strength is below AMS 5663 minimum.

If cooling rate between ageing stages is too fast (above 55°C per hour): The secondary gamma prime (γ′) precipitate does not form at the intended temperature and size distribution. The γ′ contributes to strength – too fast a cool rate produces a slightly different strength profile that may or may not meet AMS 5663 minimums depending on where the actual temperatures and rates fall.

Practical implication for Indian forging manufacturers: The ageing furnace must achieve and maintain ±8°C uniformity throughout the working zone — not just at the thermocouple location. A large furnace with poor temperature uniformity may have one zone at 718°C and another at 735°C — producing non-uniform properties across the load. AMS 2750 Temperature Uniformity Survey at the ageing temperatures (718°C and 621°C) is the verification that the furnace can achieve the required uniformity.

US aeroengine buyers specifically ask Indian Inconel 718 forging suppliers to show TUS records at 718°C and 621°C — not just at higher temperatures used for solution annealing. A supplier whose TUS records cover only 950°C and above has not validated their furnace capability at the critical ageing temperatures.

Documentation of the Double Ageing Cycle

The furnace chart for an Inconel 718 double ageing cycle should show:

Initial ramp to 718°C (Stage 1 ageing temperature)
Soak at 718°C for 8 hours — temperature should remain within ±8°C of 718°C throughout
Controlled furnace cool from 718°C to 621°C at ≤55°C per hour — the furnace chart must show this cooling rate is achieved, not just that the next setpoint is 621°C
Hold at 621°C for sufficient time that total ageing time (Stage 1 + Stage 2) equals 8 hours minimum
Air cool from 621°C

US aeroengine quality engineers who receive Inconel 718 heat treatment records look for all five elements on the furnace chart. A record that shows only the target temperatures and the total cycle duration without the continuous temperature trace showing stability and the cooling rate between stages — is inadequate for US aeroengine programme acceptance.

Delta Phase: The Microstructural Concern for US Buyers

What Delta Phase Is and Why It Matters

Delta phase (δ, Ni₃Nb with orthorhombic crystal structure) is a stable Inconel 718 phase that forms when the alloy is held in the temperature range 650–980°C. It directly competes with gamma double prime (γ″) for niobium — if delta phase forms, the niobium that would otherwise be available for γ″ precipitation strengthening is consumed, and strength is reduced.

When delta phase is beneficial: Controlled amounts of delta phase at grain boundaries – produced by deliberate thermomechanical processing in the delta phase stability range limit grain growth and provide a fine, uniform grain size that improves fatigue life. Some Inconel 718 forging specifications (particularly for aeroengine rotating components where low-cycle fatigue life is the governing design criterion) specify controlled delta phase at grain boundaries as a positive microstructural feature.

When delta phase is harmful: Excess delta phase — particularly large plate-like particles in the grain interiors — depletes niobium from the matrix, reduces the amount of γ″ that forms during ageing, and lowers both tensile strength and toughness. Forgings that were slowly cooled after forging (allowing extensive delta phase to form) or that were held too long at temperatures in the 700–900°C range may develop excess delta phase that reduces properties below AMS 5663 minimums.

How US Aeroengine Buyers Evaluate Delta Phase Capability

US aeroengine buyers evaluating Indian Inconel 718 forging suppliers assess delta phase awareness through:

Process knowledge questions:

Can the supplier’s metallurgist explain the difference between beneficial grain-boundary delta phase and harmful excess delta phase?
What is the supplier’s cooling practice after forging – how quickly does the forging reach ambient temperature, and through what temperature range?
Does the supplier monitor delta phase content metallographically, and if so, at what inspection frequency?

Metallographic capability:

Can the supplier prepare polished and etched metallographic cross-sections from Inconel 718 forgings?
Does the NABL-accredited laboratory have capability for optical microscopy at the magnification required for delta phase evaluation (200×–500×)?

Historical data:

Can the supplier provide metallographic reports from previous Inconel 718 production showing grain size and delta phase morphology?

Suppliers who can answer these questions specifically and provide documentation from previous production demonstrate genuine Inconel 718 process knowledge — not just claimed capability.

Inconel 625: The Second Key Alloy for US Aeroengine Forgings

Where Inconel 625 Is Used in US Aeroengine and Gas Turbine Programmes

Inconel 625 (UNS N06625, AMS 5666) is specified in US aeroengine programmes for applications where corrosion resistance and moderate elevated-temperature strength – rather than the maximum strength of Inconel 718 are the primary requirements:

Combustor structural components: Combustor outer casings and mounting rings experience high temperature (600–800°C) but lower structural loads than rotating components. Inconel 625 in the annealed condition provides adequate high-temperature strength with excellent oxidation resistance at these temperatures.

Structural casings: Fan case and intermediate case structural forgings which carry engine loads but rotate with the aircraft rather than at engine speed use Inconel 625 where temperature exposure limits the use of aluminium or titanium.

Exhaust system structural forgings: Jet pipe and reverser structural components in the hot section of the engine exhaust.

Industrial gas turbine structural applications: Industrial gas turbine structural casings, transition pieces, and combustor structural components in Inconel 625 where continuous high-temperature exposure and cyclic thermal stresses are the governing design considerations.

Inconel 625 Processing Solution Anneal Only

Unlike Inconel 718, Inconel 625 achieves its properties through solid solution strengthening – the chromium, molybdenum, and niobium in solid solution provide strength without precipitation hardening. No ageing treatment is required or beneficial for standard aeroengine structural applications.

Heat treatment: Solution anneal at 1,093°C–1,204°C (2,000°F–2,200°F), hold for sufficient time for temperature uniformity throughout the section, rapid cool (water quench for sections above 25mm thickness).

What the solution anneal achieves:

Dissolution of any delta phase (Ni₃Nb) formed during forging
Dissolution of carbides that precipitated at grain boundaries during slow cooling
Restoration of a uniform, fully solid-solution-strengthened microstructure

What happens without adequate solution annealing: If Inconel 625 is not properly solution annealed — insufficient temperature, inadequate hold time, or too slow a cool — carbide precipitates and Laves phase remain at grain boundaries. These precipitates reduce ductility and toughness and can serve as corrosion initiation sites in service.

US aeroengine buyers verify Inconel 625 heat treatment by reviewing furnace charts showing the annealing temperature reached, the hold time, and the cooling rate — not just a certificate stating “annealed per AMS 5666.”

Immersion UT for Inconel 718 Rotating Component Forgings

Why Immersion UT Is Required for Inconel 718 Aeroengine Discs

Contact UT — the standard method for structural forgings — is not adequate for Inconel 718 aeroengine rotating component inspection for two reasons:

Coupling variability: Contact UT coupling between the probe and the forging surface is affected by surface roughness, probe pressure, and the contact footprint. For standard structural forgings where indication amplitudes are well above the noise floor, this variability is acceptable. For Inconel 718 rotating components where AMS 2154 Class AA acceptance criteria require detection of very small defects, contact coupling variability masks indications at the required detection sensitivity.

Scanning coverage: Contact UT of complex geometry disc forgings requires multiple probe setups and scanning directions to cover the full volume. Ensuring 100% volume coverage including near-surface regions and zones near geometric discontinuities — is difficult to document with contact UT.

Immersion UT solution: Immersion UT – where the forging is submerged in water and the UT beam enters through the water column – provides consistent coupling, enables scanning from any direction without probe-surface contact, and allows automated scanning patterns that document 100% coverage.

What US Aeroengine Buyers Check for Immersion UT Capability

Immersion tank dimensions: The immersion tank must be large enough to fully submerge the largest expected disc forging with adequate clearance for probe movement around all surfaces. A disc forging 500mm in diameter requires a tank at least 800mm internal diameter and 400mm deep. Indian suppliers with immersion tanks below 600mm diameter cannot accommodate standard aeroengine disc forgings.

Automated scanning capability: Manual immersion UT cannot reliably achieve the consistent scanning pitch (spacing between adjacent scan lines) and coverage documentation required for AMS 2154 Class AA inspection. Automated or semi-automated scanning systems with position encoding that documents the probe path are required by most US aeroengine OEMs. This is a capital investment — US buyers assess whether the Indian supplier has made this investment.

Inconel 718 calibration reference standard: The reference standard for Inconel 718 rotating component immersion UT must be fabricated from Inconel 718 — not from steel. The acoustic properties (longitudinal wave velocity, acoustic impedance) of Inconel 718 differ from steel, and a calibration established with a steel reference will produce incorrect sensitivity settings for Inconel 718 inspection. US aeroengine buyers ask to see the Inconel 718 calibration standard — its material certification, the flat-bottom hole dimensions, and the current calibration records.

AMS 2154 acceptance class: AMS 2154 defines several acceptance classes — A, AA, and others with different flat-bottom hole equivalence thresholds. For rotating components (compressor discs, turbine discs, shafts), Class AA is the standard. Some OEMs specify even more stringent proprietary acceptance criteria. US buyers confirm which acceptance class the Indian supplier is qualified to inspect to, and verify this against what the programme requires.

US Aeroengine Programme Qualification for Indian Inconel Forging Suppliers

The Typical Qualification Pathway

Phase 1: AS9100D and capability verification (3–6 months) US aeroengine procurement teams verify AS9100D via OASIS, review NABL scope for Inconel-relevant testing, confirm immersion UT capability with Inconel 718 calibration standard, and confirm double-ageing furnace AMS 2750 TUS at 718°C and 621°C.

Phase 2: On-site technical assessment (3–5 months to arrange and execute) GE, P&W, or Honeywell supply chain quality engineers visit the Indian facility. Assessment covers: forging area capability demonstration, heat treatment area including furnace charts from recent Inconel 718 production, immersion UT demonstration with Inconel 718 calibration, delta phase metallographic capability, NABL laboratory review, and AS9100D quality system live assessment.

Phase 3: Qualification forgings (4–6 months) Production of 3–5 qualification Inconel 718 disc forgings of a representative geometry. Full production conditions — not enhanced controls. Complete testing: tensile, Charpy, hardness, creep and stress rupture where specified, immersion UT, FPI. Metallographic cross-sections for grain size and delta phase evaluation. AS9102 FAIR package assembled and submitted.

Phase 4: Engineering review and approval (2–4 months) OEM materials and quality engineering teams review all qualification data. For rotating component forgings, this review may involve the airworthiness authority’s DER (Designated Engineering Representative) review in some OEM’s processes.

Phase 5: Production approval First production order placed. First lot subject to enhanced inspection — 100% mechanical testing rather than sampling — with relaxation to standard sampling levels after 3–5 successful production lots.

Vinir Engineering’s Inconel Forging Capability for US Aeroengine Programmes

Vinir Engineering produces Inconel 718 and Inconel 625 forgings under AS9100D certification for defence and aerospace programmes.

Inconel 718 closed die forging: 10–1,400 kg range. Forging temperature monitoring by calibrated pyrometer. Forging temperature window documented per alloy heat. Controlled cooling after forging to manage delta phase formation.

Double ageing heat treatment: AMS 2750 calibrated furnaces with TUS records at 718°C and 621°C specifically. Continuous electronic data logging on all ageing cycles. Furnace chart retention for every production lot. Controlled furnace cooling between ageing stages documented by furnace chart.

Solution annealing for Inconel 625: 1,093–1,204°C with rapid water quench. Complete dissolution of Laves phase and carbides verified by review of previous production metallography.

UT capability: Contact UT with Inconel 718 and Inconel 625 calibration reference standards. Immersion UT capability for disc and ring geometry forgings. ASNT Level II certified operators with nickel alloy UT qualification.

Metallographic examination: NABL laboratory with optical microscopy for grain size and delta phase evaluation. ASTM E112 grain size measurement. Delta phase morphology assessment capability.

NABL-accredited testing: OES chemical analysis to AMS 5663 specified elements including niobium. Tensile testing to AMS 5663 minimum. Charpy impact. Hardness Rockwell C and Vickers.

For US aeroengine procurement teams evaluating Indian Inconel forging sources, Vinir provides a complete capability assessment package within 5 working days.

Frequently Asked Questions – Inconel Forging Supplier for US Aeroengines

What is the difference between Inconel 718 and Inconel 625 for US aeroengine forging applications? Inconel 718 is precipitation-hardenable — the double-ageing treatment develops gamma double prime (γ″) precipitates that increase yield strength to minimum 1,030 MPa. It is the standard material for rotating components (compressor and turbine discs, shafts) where high strength under centrifugal and pressure loading is the primary requirement. Inconel 625 achieves its properties through solid solution strengthening only — no ageing treatment. Its yield strength in the annealed condition is approximately 415–550 MPa — significantly lower than Inconel 718 STA. Inconel 625 is specified for structural casings, combustor components, and applications where corrosion resistance and fabricability (weldability) are more important than maximum strength. The two alloys are not interchangeable in aeroengine applications.

Why is AMS 2750 furnace calibration specifically at the ageing temperatures (718°C and 621°C) important?
AMS 2750 Temperature Uniformity Surveys verify that the furnace achieves the specified temperature uniformity (typically ±8°C for Class 2 or ±6°C for Class 1 furnaces at the working temperature) throughout the working zone at the actual operating temperature. A furnace that achieves ±8°C at 1,000°C may have significantly worse uniformity at 718°C if the heating elements and control systems are optimised for higher temperatures. The TUS must be conducted at each temperature at which the furnace is used for production — a TUS at 950°C does not validate the furnace for Inconel 718 ageing at 718°C. US aeroengine buyers specifically request TUS records at the ageing temperatures because inadequate furnace uniformity at 718°C is the most common cause of Inconel 718 strength non-conformance in production.

What is AMS 2154 Class AA and why is it specified for Inconel 718 rotating component forgings?
AMS 2154 — Inspection, Ultrasonic, Wrought Metals — defines the ultrasonic inspection method and acceptance criteria for aerospace wrought metal products including forgings. Class AA is the most stringent acceptance class defined in AMS 2154 — it specifies detection sensitivity calibrated to flat-bottom holes (FBH) of specified diameter at specified depths in the Inconel 718 forging cross-section. Class AA is specified for rotating components because any internal discontinuity — inclusion, void, segregation — that exceeds Class AA size limits is considered capable of initiating a fatigue crack that could propagate to disc fracture under the cyclic loading of aeroengine operation. The consequence of rotating component disc fracture — release of disc fragments at operating speed — is a catastrophic safety event that drives the most stringent inspection requirements applied to any industrial forging.

Can Indian forging manufacturers obtain NADCAP accreditation for Inconel 718 heat treatment and UT?
Yes. NADCAP accreditation is available to any manufacturing facility globally that meets the NADCAP audit criteria for the relevant special process. For heat treatment (NADCAP AC7102) and NDT (NADCAP AC7114), Indian facilities are eligible for audit and accreditation by the Performance Review Institute. The NADCAP audit process for heat treatment requires demonstration that all furnaces used for aerospace heat treatment comply with AMS 2750 including current TUS and SAT records, that all heat treatment procedures are controlled documents, and that pyrometer calibration is maintained. The audit is rigorous — typically requiring 12–18 months of preparation — but the resulting accreditation is recognised by all US aerospace OEMs as equivalent to domestic US NADCAP accreditation.

What is the typical value of Inconel 718 forging content in a modern high-bypass turbofan engine?
A modern high-bypass turbofan engine such as the GE9X (Boeing 777X) or PW1000G GTF (Airbus A320neo) contains 20–40 distinct Inconel 718 forged components — compressor discs, turbine discs, engine shafts, seal discs, and structural rings. Individual forging values range from $5,000 for smaller structural rings to $150,000–250,000 for large high-pressure turbine discs. Total Inconel 718 forging content per engine is typically $1.5–4 million depending on engine size and thrust class. Over a production run of several thousand engines per programme, the cumulative Inconel 718 forging demand represents billions of dollars — and a percentage of this demand that an Indian forging manufacturer can capture by qualifying for even one engine programme represents substantial long-term revenue.

Inconel Forging Supplier for US Aeroengine and Gas Turbine Programmes

At a Glance: Inconel Forging Requirements for US Aeroengine Programmes