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They also have secondary hardening and machining as required after being made.

It is a misconception that the blade needs to be attached to a shaft that spins as the blade moves or spins in the plain of the belt that they are attached to a belt, acts as a summing of the wind forces that are pushing on the blades. The number of blade count increase from one to a sum that no long increases the force that is collected from the speed of the traveling wind.
The rotation takes place around the center of the struction that has pulleys that attach to the structure that alowws for the belt to move around it as the blade is pushed.
The belt allows for slow rpm wind to create power based on ratio of the belt length to shaft of the generator circumference. This is simular to that of an engine crank shaft to that of the alternator pulleys for ratio.
The rpm is measure and timed from a single point on the belt to get a number for the ratio of spin that the genrator will rquire.

Wind power is generated by the force wind exerts on the blades of a turbine, causing the turbine’s shaft to rotate at a speed of 10 to 20 revolutions per minute (rpm). To produce power efficiently, wind turbines require wind speeds above seven miles per hour for electricity generation

Wind Speed and RPM for1 kW Power Output
The wind speed and rotational speed (RPM) required to produce 1 Kw of power from a wind turbine are dependent on several factors, including the turbine's design, size, and the specific wind conditions.

Factors Influencing Power Output
Turbine Size and Design: Smaller wind turbines, often used in residential settings, typically require higher RPMs to generate power compared to larger, utility-scale turbines. This is because larger turbines compensate for slower rotation with longer blades, which capture more wind and have a greater swept area.

Wind Speed: The power produced by a wind turbine is directly related to the cube of the wind speed. This means that a small increase in wind speed can lead to a significant increase in power output. For example, if the wind speed doubles, the power output can increase by a factor of 2^3=8.

Tip Speed Ratio (TSR): The TSR is the ratio of the speed of the blade tip to the wind speed. Wind turbines are designed to operate efficiently within a specific TSR range, which influences the optimal RPM for power generation at a given wind speed.

Generator Requirements: Most generators require a specific rotational speed, often in the range of 1,000 to 1,800 RPM to produce electricity at the desired frequency of 50 to 60 hz.

Gearboxes are commonly used in wind turbines to increase the relatively slow rotational speed of the blades to the higher speed required by the generator.

Typical RPM Ranges for 1Kw Turbines
For small wind turbines, such as those rated for 1 Kw the rotor RPM typically falls within the range of 200 to 400 RPM to begin generating electricity. The exact RPM at which 1 Kw to begin generating electricity is produced will vary based on the specific turbine model and the prevailing wind speed.

torque and speed to generator 1kw of powerThinkingKicking off 5 searchesLooking at 77 sitesPutting it all together To produce 1 kilowatt (kW) of power, the required torque and speed are inversely related, meaning there isn't one single combination. You can use a high torque with low speed or low torque with high speed to achieve the same power output. The specific values depend on the generator's design and operating efficiency. Key relationship The fundamental relationship is expressed by the mechanical power formula:P=\tau \cdot \omega where: P is mechanical power in watts (W).\tau  is torque in newton-meters (N·m).\omega  is angular velocity in radians per second (rad/s). Since 1 kW is 1000 W, the ideal mechanical input power required is 1000 W. For a real-world generator, you must account for its efficiency, which will require a higher mechanical input than the electrical output. Calculating torque and speed To determine the values for torque (\tau ) and speed (n), you must choose one variable and calculate the other.

The formulas below include the constant for converting revolutions per minute (rpm) to radians per second. With revolutions per minute (rpm)\tau [N\cdot m]=9550\cdot \frac{P[kW]}{n[rpm]}n[rpm]=9550\cdot \frac{P[kW]}{\tau [N\cdot m]}
Note:
These formulas assume 100% efficiency. For a real-world generator, you must divide the output power by the generator's efficiency (e.g., 0.8 for 80% efficiency). 

Example calculations for a 1 kW output:
The table below shows example torque values for a range of common speeds, assuming an 85% generator efficiency.Input Power (ideal): 1kW=1000WInput Power (with 85% efficiency): 1000W/0.85\approx 1176W Generator Speed (n) Input Torque (\tau )Calculation Example50 rpm224 N·m(9550\times 1.176)/50300 rpm37.3 N·m(9550\times 1.176)/300900 rpm12.4 N·m(9550\times 1.176)/9001800 rpm6.2 N·m(9550\times 1.176)/18003600 rpm3.1 N·m(9550\times 1.176)/3600

Factors that influence the required torque and speed Generator efficiency:

Real generators are not 100% efficient.
The mechanical input power must be greater than the electrical output power to overcome losses from friction, heat, and electrical resistance.

Prime mover:
The specific combination of torque and speed will also be influenced by the driving power source (e.g., a motor, wind turbine, or water turbine), which has its own torque-speed characteristics.

Application:
The required speed may be fixed for certain applications. For example, to produce 60 Hz power, many generators must operate at a specific synchronous speed, such as 1800 rpm or 3600 rpm.

seems this is a choice

Wikipedia
https://en.wikipedia.org › wiki › RL10
Thrust (altitude): 24,750 lbf (110.1 kN) · Specific impulse: 465.5 seconds (4.565 km/s) · Engine weight, dry: 664 lb (301.2 kg) · Height: 163.5 in (4.14 m) ...
AI Overview

+7
The RL10 is a high-performance, liquid-fueled upper-stage rocket engine from Aerojet Rocketdyne that uses liquid hydrogen and liquid oxygen (LH2/LOX) propellants. Key specifications include thrusts around 25,000 pounds (110 kN) for models like the RL10B-2, very high specific impulses of over 465 seconds, and an expander cycle. The engine's performance is highly reliable and it has been continuously upgraded for missions like NASA's Space Launch System (SLS) and commercial launchers such as Atlas and Delta.
Key Specifications (RL10B-2 Model):
Thrust: 24,750 lbf (110 kN)
Specific Impulse (Isp): 465.5 seconds (4.565 km/s)
Engine Weight (dry): 664 lb (301.2 kg)
Propellants: Liquid Hydrogen (LH2) and Liquid Oxygen (LOX)
Cycle Type: Expander Cycle
Propellant Mixture Ratio: ~5.88 to 1 (Oxygen:Hydrogen by mass)
Key Features and Development
High Performance:
The RL10 is the world's highest-performance upper-stage rocket engine, known for its high efficiency thanks to its expander cycle and expandable nozzle.
Reliability:
It has a long history of reliable operation, with millions of accumulated hot-fire seconds and a demonstrated reliability of 0.9998.
Evolution:
The engine family has been continuously upgraded since its original design for the Centaur upper stage. Modern versions incorporate features like 3D printing and extendable nozzles for improved performance.
Applications:
The RL10 powers upper stages for various launch vehicles, including the Space Launch System (SLS) Interim Cryogenic Propulsion Stage (ICPS) and Exploration Upper Stage (EUS), as well as ULA's Atlas and Delta rockets and the Vulcan Centaur.
Manufacturing:
Recent advancements involve using 3D printing to create components from materials like copper, which enables complex geometries not possible with traditional methods.

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Lockheed's first-stage flyback booster

The Artemis rocket's RS-25 core stage engines are fueled by a liquid hydrogen (LH2) and liquid oxygen (LOX) propellant combination, chosen for its superior specific impulse. Liquid hydrogen serves as the primary fuel, while liquid oxygen acts as the oxidizer, providing the necessary thrust to power the Space Launch System (SLS) rocket.
Fueling Process
Liquid Hydrogen:
.
A large volume of liquid hydrogen is stored in a cryogenic tank within the SLS core stage and is cooled to extremely low temperatures of -423 degrees Fahrenheit.
Liquid Oxygen:
.
Liquid oxygen is also stored in a cryogenic tank, with a separate tank and line running around the hydrogen tank.
Turbopumps:
.
Due to the vastly different densities and flow rates of liquid hydrogen and liquid oxygen, the RS-25 engines use two separate turbopumps to manage each propellant.
Combustion:
.
Both the fuel and oxidizer are fed into the RS-25 engines to produce thrust for the Artemis missions.
Key Considerations
Cryogenic Challenges:
.
Liquid hydrogen's extremely low temperature makes it difficult to work with, requiring well-insulated tanks and careful handling to prevent leaks and maintain the liquid state.
Efficiency:
.
The LOX/LH2 combination is used because it offers the maximum possible energy for the fuel's weight, providing a highly efficient engine.
New Engines for Future Missions:
.
While the first Artemis missions use modified space shuttle RS-25 engines, NASA is now producing new RS-25 engines for future missions, starting with Artemis V, to ensure a continued supply for the SLS program

The second stage of the Artemis rocket, known as the Interim Cryogenic Propulsion Stage (ICPS), is fueled with liquid hydrogen (LH2) and liquid oxygen (LOX) to power its single RL10 engine, providing the necessary boost to send the Orion spacecraft towards the Moon. It also carries hydrazine for its Reaction Control System (RCS), used for orientation and stabilization in space.
Details of the ICPS (Second Stage):
Propellants:
The main propellant for the ICPS engine is a combination of liquid hydrogen (LH2) and liquid oxygen (LOX).
Engine:
The RL10 engine is used in this stage, with the Artemis 2 mission debuting a newer RL-10C2 model.
Purpose:
After the SLS core stage and Solid Rocket Boosters (SRBs) complete their burn and separate, the ICPS uses its RL10 engine to provide the Trans-Lunar Injection (TLI) burn, sending the Orion spacecraft out of Earth's orbit and toward the Moon.
Hydrazine:
In addition to its main engine fuel, the ICPS carries hydrazine for its Reaction Control System, which is used for small attitude adjustments and maneuvering in space.
Fueling Process:
1. Preparation:
The ICPS is transported to NASA's Kennedy Space Center and then to the Vehicle Assembly Building (VAB).
2. Fueling:
Technicians then fuel the ICPS with its required propellants, including liquid hydrogen, liquid oxygen, and hydrazine.
3. Integration:
The ICPS is then mated with the rest of the SLS rocket elements for launc

Atlas rocket stages use different fuels depending on the component: the main first stage (or core) uses liquid oxygen and RP-1 (kerosene). The upper stage, the Centaur, uses liquid oxygen and liquid hydrogen, which is a highly efficient propellant. Strap-on boosters, when used, are solid rocket motors containing a form of solid fuel.
First Stage (Booster)
Propellant: Liquid oxygen (LOX) and RP-1 (a refined kerosene).
Engine(s): A single, Russian-made RD-180 engine powers the first stage of the Atlas V. Older Atlas versions used various Rocketdyne engines.
Second Stage (Upper Stage)
Propellant: Liquid oxygen (LOX) and liquid hydrogen (LH2).
Engine(s): The Centaur upper stage uses one or two Aerojet Rocketdyne RL10 engines. This liquid-hydrogen fueled stage is known for its high efficiency and ability to be restarted in space.
Strap-on Solid Rocket Boosters (SRBs)
Propellant:
A solid fuel containing powdered aluminum and an oxidizer called ammonium perchlorate.
Function:
These are added to the Atlas V to provide additional liftoff thrust for heavier payloads, and can be configured in different numbers depending on the mission

The second stage engine for the Atlas rocket (specifically the Atlas V and its predecessors, known as the Centaur upper stage) is powered by a combination of liquid hydrogen (fuel) and liquid oxygen (oxidizer). These cryogenic propellants are burned in an Aerojet Rocketdyne RL10 engine, which is known for its high energy and restart capability.
Here's a breakdown:
Propellant:
The RL10 engine uses liquid hydrogen as its fuel and liquid oxygen as its oxidizer.
Engine Type:
The engine is the RL10, a high-energy, American-made engine manufactured by Aerojet Rocketdyne (formerly Pratt & Whitney).
Function:
This high-energy propellant combination is ideal for upper stages like the Centaur, allowing it to efficiently place payloads into orbit with high precision.
Handling:
Liquid hydrogen is a very high-energy fuel but also a cryogenic fluid with significant handling challenges

The first stage of the Vulcan rocket uses liquefied natural gas (methane) and liquid oxygen as fuel, powered by two Blue Origin BE-4 engines, while its Centaur V upper stage uses liquid hydrogen and liquid oxygen for its Aerojet Rocketdyne RL10 engines. Solid rocket boosters can also be attached to the first stage for additional thrust at liftoff.
The Vulcan rocket's second stage, known as the Centaur V, is powered by two Aerojet Rocketdyne RL10 engines that run on liquid hydrogen and liquid oxygen fuel. These engines are designed to precisely place payloads into orbit by providing the energy for the final stages of the mission.
First Stage
Engines: Two Blue Origin BE-4 engines.
Fuel: Liquefied natural gas (methane) and liquid oxygen.
Purpose: To lift the rocket off the launch pad and provide power for the initial phase of flight.
Second Stage (Centaur V)
Engines: Two Aerojet Rocketdyne RL10 engines.
Fuel: Liquid hydrogen and liquid oxygen.
Purpose: To provide precise, restartable thrust to accurately place payloads into their intended orbits.
Solid Rocket Boosters (Optional)
Fuel: Graphite-epoxy composite.
Purpose: To provide extra thrust during liftoff for heavier payloads.

Key details about the second stage:
Name: Centaur V
Engines: Two Aerojet Rocketdyne RL10C engines
Fuel: Liquid hydrogen (LH₂) and liquid oxygen (LO₂)
Purpose: To provide the precise final orbital insertion and high-energy orbits needed for complex payloads.
Manufacturer: Aerojet Rocketdyne is the manufacturer of the RL10 engine.

first video Rocket engine performance (specific impulse) table

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The good news is

seems like it was heavy to move and it sure looks more robust.