According to the invention, the blade (4) comprises a blade body (5) and a blade root (6).
The rotor blade includes a blade root arranged within the slot.
A wind turbine rotor blade root load sensor is provided.
The screw blade comprises a working surface (1), a blade tip (2) and a blade root (3).
The invention relates to a wind turbine rotor blade (100), comprising a rotor blade root (110), a rotor blade tip (120), a rotor blade front edge (160), a rotor blade rear edge (170), a pressure side (140), and a suction side (130).
The blade further includes an attachment root (124).
The fuselage and wing roots s' flared immediately.
The present disclosure relates to composite airfoils bonded to a metallic root.
The leading edge wing root merged with the top of the fuselage and cockpit.
The rotor blade may include an airfoil that extends from a connection with a root.
The mast and the mast-step (14) are articulated at (15-16) to the frame.
A movable mast (4) is attached to a boat's (1) inner bottom hull via a sideways movable step (12).
A blade (11) of a ceiling fan is integrally formed from a root portion (12), a blade portion (13), and a step portion (14) that maintains the blade portion (13) in a state inclined from a horizontal state.
The single-place cockpit, set in line with the wing root, was 15 ft (4.6 m) off the ground when the airplane was parked.
The aircraft's two fuel shutoff valves, one in each wing root, were found with one in the fully open position, and one in a partially open position.
The airfoil structure further comprises of a leading edge (120), a trailing edge (125), a left edge (130), a right edge (135), a central wing root (140), and a plurality of chord lines (145).
The two General Electric J33-GE-5 turbojet engines were located in each wing root, which left the large and bulky fuselage free for fuel tanks and armament.
The invention relates to a gas turbine vane, especially a vane pertaining to an aircraft engine, comprising a blade (11) and a vane footing (12).
The console or the floor is provided with a mast foundation hole and with a center board well.
Each blade consists of a blade footing (1), a blade profile (2) and a cover plate (3), wherein said blade footings (1) of the blade row are densely adjacently integrated into the rotor (4) slots.
A thermal coating extends from the root section of the airfoil toward the tip section of the airfoil.
A wheel for a rotating flow machine, comprising a rotor (1) on which a plurality of blades (2) are arranged projecting radially from the rotor (1), with each blade (2) having a root (3) attached to the rotor (1) and a blade top (4).
The rotor blade further extends in a generally span-wise direction between a root and a tip.
An aircraft structure extending from a root to a tip, the root being adapted to be joined to an aircraft fuselage.
Each of the blades includes a root (66), a tip (70), a leading edge (74) between the root and the tip, and a trailing edge (78) between the root and the tip.
The inventive rotating blade (10) is provided with a front of blade (11) and a footing of blade (12) connected thereto.
The root section (1) of the turbine blade is designed to fit within precise tolerances upon a circular rotor.
A composite blade assembly is disclosed including a composite blade or aerofoil (2) and a root member (1).
Said system comprises a blade footing (12) that is retained on a blade holder (14) against the forces acting on the blade.
Each root (27) is connected with one of the grooves (G) to mount the twin fins (21) to the core (11).
Most of the propeller blades separated at the root, and a portion of a blade penetrated the cabin wall.
One particular blade was fractured near the airfoil root platform, and the topography of the fracture surface showed signs of fatigue cracking.
Requêtes fréquentes français :1-200, -1k, -2k, -3k, -4k, -5k, -7k, -10k, -20k, -40k, -100k, -200k, -500k, -1000k,
Requêtes fréquentes anglais :1-200, -1k, -2k, -3k, -4k, -5k, -7k, -10k, -20k, -40k, -100k, -200k, -500k, -1000k,
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