A blade, for a rotor of an aircraft, comprising a hollow cylindrical sleeve, a stop fastened to the cylindrical sleeve, a profiled portion, and an anchoring device, a blade body and a hollow torsion box secured to the profiled portion. The anchoring device and the blade body are positioned inside the cylindrical sleeve. The anchoring device surrounds the stop in order to form a stop for the profiled portion parallel to a longitudinal axis of the blade. The hollow torsion box is secured to the profiled portion, and comprises a bearing zone in contact with an inner wall of the cylindrical sleeve, taking up the bending loads on the blade.

An aircraft propeller, including a propeller shaft and propeller blades or propeller airfoils secured on the propeller shaft, wherein an inlet-side flow channel and an outlet-side flow channel are introduced into each of the propeller blades or each of the propeller airfoils, wherein each inlet-side flow channel has an inlet opening and each outlet-side flow channel has an outlet opening on each of the propeller blades or propeller airfoils, wherein each inlet-side flow channel has a connection to the outlet-side flow channel of a respective other propeller blade or propeller airfoil such that air flowing in via the inlet-side flow channel flows out via the outlet-side flow channel of the respective other propeller blade or propeller airfoil, and wherein the inlet opening and the outlet opening of each propeller blade or propeller airfoil are arranged on different sides of the propeller blade or propeller airfoil.

An aircraft propeller, including a propeller shaft and propeller blades or propeller airfoils secured on the propeller shaft, wherein an inlet-side flow channel and an outlet-side flow channel are introduced into each of the propeller blades or each of the propeller airfoils, wherein each inlet-side flow channel has an inlet opening and each outlet-side flow channel has an outlet opening on each of the propeller blades or propeller airfoils, wherein each inlet-side flow channel has a connection to the outlet-side flow channel of a respective other propeller blade or propeller airfoil such that air flowing in via the inlet-side flow channel flows out via the outlet-side flow channel of the respective other propeller blade or propeller airfoil, and wherein the inlet opening and the outlet opening of each propeller blade or propeller airfoil are arranged on different sides of the propeller blade or propeller airfoil.

An aircraft blade assembly, including: a blade extending from a blade root to an opposite tip; and a heat exchanger disposed on at least a portion of a leading edge of the blade, the heat exchanger including: a first arcuate panel shaped to conform to the leading edge of the blade; and a second arcuate panel mated with the first arcuate panel; wherein at least one of the first and second arcuate panels includes a channel formed thereon to form a fluid passage between the first and second arcuate panels.

An aircraft blade assembly, including: a blade extending from a blade root to an opposite tip; and a heat exchanger disposed on at least a portion of a leading edge of the blade, the heat exchanger including: a first arcuate panel shaped to conform to the leading edge of the blade; and a second arcuate panel mated with the first arcuate panel; wherein at least one of the first and second arcuate panels includes a channel formed thereon to form a fluid passage between the first and second arcuate panels.

A fan blade comprising a blade body spanning from a blade root to a blade tip in a longitudinal direction and a fluid passageway formed within the blade body and extending from the blade root to the blade tip. The blade body spanning from a leading edge to a trailing edge in a lateral direction. The fluid passageway allowing fluid to flow out of the blade.

A fan blade comprising a blade body spanning from a blade root to a blade tip in a longitudinal direction and a fluid passageway formed within the blade body and extending from the blade root to the blade tip. The blade body spanning from a leading edge to a trailing edge in a lateral direction. The fluid passageway allowing fluid to flow out of the blade.

The invention relates to design and production methods for a rotor which is both a turbine and a propeller having blades that are hollow along the entire length thereof and which lead into peripheral circular chambers that operate as an engine (THRA) that can be powered by working fluids.

The invention relates to design and production methods for a rotor which is both a turbine and a propeller having blades that are hollow along the entire length thereof and which lead into peripheral circular chambers that operate as an engine (THRA) that can be powered by working fluids.

An aircraft propeller, including a propeller shaft and propeller blades or propeller airfoils secured on the propeller shaft, wherein an inlet-side flow channel and an outlet-side flow channel are introduced into each of the propeller blades or each of the propeller airfoils, wherein each inlet-side flow channel has an inlet opening and each outlet-side flow channel has an outlet opening on each of the propeller blades or propeller airfoils, wherein each inlet-side flow channel has a connection to the outlet-side flow channel of a respective other propeller blade or propeller airfoil such that air flowing in via the inlet-side flow channel flows out via the outlet-side flow channel of the respective other propeller blade or propeller airfoil, and wherein the inlet opening and the outlet opening of each propeller blade or propeller airfoil are arranged on different sides of the propeller blade or propeller airfoil.