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.