You've seen this image do the rounds. The story goes Gas turbines blades - 5 years booked - single crystal blade technology - only 3 companies etc. Yes & No. Here's a no nonsense, first principles breakdown: Firstly, Single crystal blades are used in a gas turbines (power) or a jet engines SPECIFICALLY where temperatures exceed 1,600°C A single crystal blade is a piece of metal made of one continuous grain of nickel superalloy. No grain boundaries, no weak seams. That is why it can survive 1,600°C gas at 10,000 g of centrifugal force for 30 years. But SC blades for Jet engines vs power turbines are very different. Same process but very different. In a jet engine, the single-crystal blade is the Stage 1 rotor of the high-pressure turbine. It is roughly 10 centimetres long and weighs a few hundred grams. It spins at 15,000 to 20,000 RPM. It runs in cycles, takeoff to landing, ten times a day. What kills a jet blade is fatigue i.e - The slow weakening of metal under repeated cycles of stress and temperature change. A power turbine Stage 1 blade is roughly 20 to 30 centimetres long, including the root and shank. It weighs 1.5 to 5 kilograms It spins at a steady 3,000 to 3,600 RPM. It does not cycle, it sits in 1,600°C gas continuously for months. What kills a power turbine blade is creep i.e - The slow stretching of metal under continuous heat and centrifugal force, year after year. Different killer = different alloy. Power turbine blades carry more rhenium for creep resistance. AND Different size means different physics. Growing a defect-free single grain through a 30 cm volume is multiple times harder than through a 10 cm one. Casting yields are lower. That's WHY the number of facilities that can do IGT-grade SC reliably is much smaller than the number that can do aero-grade. EVEN Within gas turbines we have F-class, H-class, J-class and theese Gas turbines for power generation are sorted by firing temperature. Meaning, higher firing temperature means higher efficiency, which means more electricity per cubic metre of gas. 1. F-class (mature, 1990s onwards) fire at around 1,300°C with combined-cycle efficiency of 58 to 60%. 2. H-class / HA-class (2000s onwards) fire at 1,450 to 1,500°C with combined-cycle efficiency of 60 to 63%. 3. J-class / JAC-class fire at around 1,600°C with combined-cycle efficiency of 63 to 64%, using rhenium-rich alloys at the absolute limit of metallurgy. As firing temperature rises, the metallurgy gets harder. The reason customers want H and J, not F is that each generation jump cuts fuel cost by 5 to 8% per MWh. For a 1 GW base-load plant, that is over ~₹1,000 crore in fuel savings every year. Every utility, hyperscaler, and LNG developer specifying new capacity wants H-class or J-class, not F. WHERE IS THE BOTTLENECK TODAY FOR GAS TURBINES? F-class capacity has plenty of headroom. Customers do not want F. H-class and J-class capacity are the constrained ones. Howmet's IGT-grade Stage 1 single-crystal line for H and J class is sold out. The in-house casting lines at GE Auburn, Siemens Berlin, and MHI Takasago are sold out. WHO CAN ACTUALLY MAKE THEM? For aero, capable countries number about 8. For heavy-duty power turbines, the commercial club drops to 3 as far as ROW is concerned. GE Vernova in the US, Siemens Energy in Germany, Mitsubishi Power in Japan + China & Russia have turbines that perform with varying performance parameters. Hope this was insightful. If you're still reading. follow and repost. Tc.