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372results about How to "Overcome or mitigate technical deficiencies" patented technology

Stator blade angle adjusting mechanism and stator casing structure with same

The invention belongs to the field of gas compressor stator blade angle adjustment design, and particularly relates to a stator casing structure. The stator casing structure is characterized by comprising a stator casing, a plurality of stator blades, a stator blade angle adjusting mechanism and a linkage ring; a plurality of mounting holes distributed in the circumferential direction are formed in the stator casing; the plurality of stator blades are distributed in the stator casing in the circumferential direction; the shaft diameter of each stator blade correspondingly extends out of one mounting hole; the stator blade angle adjusting mechanism comprises a plurality of rocker arms, and one end of each rocker arm is correspondingly connected with one shaft diameter; the linkage ring sleeves the periphery of the stator casing and is hinged to the other end of each rocker arm; each rocker arm can rotate relative to the linkage ring and can slide in the circumferential direction of thelinkage ring; and the linkage ring can move in the axial direction of the stator casing so as to drive all the rocker arms to move, and therefore the stator blades can rotate. In addition, the invention relates to the stator blade angle adjusting mechanism, and the stator blade angle adjusting mechanism has all characteristics of the stator blade angle adjusting mechanism in the stator casing structure.
Owner:AECC SHENYANG ENGINE RES INST

Two-dimensional thrust vectoring nozzle outer cover structure and design method thereof

The invention belongs to the technical field of two-dimensional thrust vectoring nozzle outer cover design, and particularly relates to a two-dimensional thrust vectoring nozzle outer cover structure. The two-dimensional thrust vectoring nozzle outer cover structure comprises a rear-section annular cover, a middle-section annular cover and a front-section annular cover, wherein the rear-section annular cover sleeves the periphery of a two-dimensional thrust vectoring nozzle, the tail end is connected with the outlet end of the expanding section of the two-dimensional thrust vectoring nozzle, and a set angle alpha is formed between the tail end and the expanding section. The middle-section annular cover sleeves the periphery of the two-dimensional thrust vectoring nozzle, the tail end of the middle-section annular cover is rotationally connected with the front end of the rear-section annular cover, and the inner side of the middle-section annular cover is rotationally connected with the expanding section. The front-section annular cover sleeves the periphery of the two-dimensional thrust vectoring nozzle, the tail end of the front-section annular cover is partially overlapped with the front end of the middle-section annular cover and is in sliding connection with the middle-section annular cover, and the inner side of the front-section annular cover is rotationally connected with the round-to-square section of the two-dimensional thrust vectoring nozzle. In addition, the invention relates to a design method of the two-dimensional thrust vectoring nozzle outer cover structure.
Owner:AECC SHENYANG ENGINE RES INST

Adjustable jet pipe structure

The invention belongs to the technical field of jet pipe structure design, and particularly relates to an adjustable jet pipe structure. The adjustable jet pipe structure comprises a jet pipe connecting cylinder, an adjusting sheet and actuating cylinders; the outer wall of the jet pipe connecting cylinder is provided with a reverse thrust exhaust port, the reverse thrust exhaust port is inclined towards the inlet end of the jet pipe connecting cylinder, and the adjusting sheet is arranged at the outlet end of the jet pipe connecting cylinder and is in sliding connection with the jet pipe connecting cylinder; the actuating cylinders are hinged between the jet pipe connecting cylinder and the adjusting sheet so as to drive the adjusting sheet to slide relative to the jet pipe connecting cylinder, and then the actuating cylinders have a forward thrust state and a reverse thrust state; in the forward thrust state, the adjusting sheet moves to slide relative to the jet pipe connecting cylinder, the effective area for shielding the outlet end of the jet pipe connecting cylinder is gradually reduced, the effective area for shielding the reverse thrust exhaust port is gradually increased, and finally, the effective area of the reverse thrust exhaust port can be completely shielded; and in the reverse thrust state, the adjusting sheet moves to slide relative to the jet pipe connecting cylinder, the effective area for shielding the reverse thrust exhaust port is gradually reduced, the effective area for shielding the outlet end of the jet pipe connecting cylinder is gradually increased, and finally, the effective area of the outlet end of the jet pipe connecting cylinder can be completely shielded.
Owner:AECC SHENYANG ENGINE RES INST

Hole plugging structure and casing hole plugging structure thereof

The invention belongs to the technical field of casing hole plugging design, and particularly relates to a hole plugging structure. The hole plugging structure comprises a mounting cylinder, a plugging pin and a spring, wherein two axial guide grooves, two circumferential guide grooves and a limiting bulge are arranged on the inner wall of the mounting cylinder; one end of each circumferential guide groove is correspondingly communicated with one axial guide groove; and two guide bulges are arranged on the outer wall of the plugging pin. The hole plugging structure has a hole plugging state and a non-hole-plugging state; when the hole plugging structure is in the hole plugging state, each guide bulge is correspondingly clamped in one circumferential guide groove, one end of the plugging pin extends out of the mounting cylinder, one end of the spring abuts against the limiting bulge, and the other end of the spring abuts against one or two guide bulges; and when the hole plugging structure in the non-hole-plugging state, the plugging pin rotates, so that each guide bulge is separated from the corresponding circumferential guide groove, enters the corresponding axial guide groove andmoves along the corresponding axial guide groove under the pushing of the spring, and the end, extending out of the mounting cylinder, of the plugging pin retracts. In addition, the invention relatesto a casing hole plugging structure with the hole plugging structure.
Owner:AECC SHENYANG ENGINE RES INST

Stator blade rotating angle adjusting and measuring structure and calibration method thereof

The invention belongs to the technical field of gas compressor stator blade rotating angle measuring, and particularly relates to a stator blade rotating angle adjusting and measuring structure. The stator blade rotating angle adjusting and measuring structure comprises multiple rocker arms, a linkage ring, a pointer and a graduated disc, wherein one end of each rocker arm is correspondingly connected with a part, extending of a gas compressor case, of one stator blade, the linkage ring is connected with the other ends of the rocker arms, is mounted on the gas compressor case in a sleeving manner, can rotate in the circumferential direction of the gas compressor case and drives the rocker arms to swing synchronously, therefore, all stator blades can synchronously rotate, accordingly, angles of the stator blades can be synchronously adjusted, the pointer is connected with one rocker arm, and can swing along with the rocker arm, the graduated disc is mounted on the gas compressor case soas to mark the swing amplitude of the pointer, and the rotating angles of the stator blades can be obtained. In addition, the invention further relates to a calibration method of the stator blade rotating angle adjusting and measuring structure.
Owner:AECC SHENYANG ENGINE RES INST

Variable-camber wing leading edge functional strength test load loading device

The invention belongs to the technical field of variable-camber wing leading edge functional strength tests, and particularly relates to a variable-camber wing leading edge functional strength test load loading device which comprises: a supporting frame used for being connected to a variable-camber wing leading edge; a deformation driving motor which is connected to the supporting frame and used for being connected to a driving connecting rod mechanism at the root of the front edge of the variable-camber wing so as to apply a deformation load to the front edge of the variable-camber wing; an upper airfoil aerodynamic load loading actuator cylinder, wherein the cylinder body of theupper airfoil aerodynamic load loading actuator cylinder is connected to the supporting frame in a sliding mode, and a piston rod of the upper airfoil aerodynamic load loading actuator cylinder is used for being connected to the upper airfoil of the front edge of the variable-camber wing so that aerodynamic loads can be applied in the normal direction of the upper airfoil of the front edge of the variable-camber wing; a lower airfoil aerodynamic load loading actuator cylinder, wherein a cylinder body of the lower airfoil aerodynamic load loading actuator cylinder is connected to the lower portion of the supporting frame in a sliding mode, and a piston rod of the lower airfoil aerodynamic load loading actuator cylinder is used for being connected to the lower airfoil of the front edge of the variable-camber wing so that aerodynamic loads can be applied in the normal direction of the lower airfoil of the front edge of the variable-camber wing.
Owner:CHINA AIRPLANT STRENGTH RES INST

Intermediate case structure

The invention relates to an intermediate case structure which comprises an intermediate case, a front shunting ring, an outer ring, an inner ring, a plurality of support plates, a rear shunting ring,a plurality of duct converting valves, a plurality of rotary shafts and an actuating mechanism; the front shunting ring is arranged in the intermediate case; the outer ring is in butt joint with the front shunting ring; the inner ring is arranged in the outer ring; one end of each of the support plates is connected with the intermediate case, the other end thereof is connected with the inner ring,and a gap is formed in the side, back on to the inlet end of the intermediate case; the rear shunting ring is clamped in all gaps and is positioned between the outer ring and the inner ring; each ofthe duct converting valves is hinged to the front shunting ring, and conical gears are arranged on the duct converting valves; one conical gear is arranged at one end of each of the rotary shafts; theconical gear on each of the rotary shafts is meshed with the conical gear on the corresponding duct converting valve; the actuating mechanism is arranged on the intermediate case and is connected with the other end of each of the rotary shafts to drive all rotary shafts to rotate, so that the duct converting valves rotate, and the intermediate case structure has the outer duct closing state and the outer duct opening state; when the intermediate case structure is in the outer duct closing state, the duct converting valves are in lap joint with the rear shunting ring; and when the intermediatecase structure is in the outer duct opening state, the duct converting valves are separated from the rear shunting ring.
Owner:AECC SHENYANG ENGINE RES INST

Intermediate case assembly

The invention relates to an intermediate case assembly. The intermediate case assembly comprises an intermediate case, a front shunt ring, an outer ring, an inner ring, a plurality of support plates,a plurality of duct conversion valves, a plurality of adjusting rods and an actuating mechanism, wherein the front shunt ring is arranged in the intermediate case; the outer ring is connected with thefront shunt ring in a butt joint mode; the inner ring is arranged in the outer ring; one end of each support plate is connected with the intermediate case, the other end of each support plate is connected with the inner ring, and a notch is formed in one side, face back onto the inlet end of the intermediate case, of each support plate; a rear shunt ring is clamped into the notches; the pluralityof duct conversion valves are hinged to the front shunt ring; the two sides of each duct conversion valve are in sealing contact with the corresponding two adjacent support plates; one end of each adjusting rod is hinged to the corresponding duct conversion valve; the actuating mechanism is arranged on the intermediate case and hinged with the other end of each adjusting rod so as to drive each adjusting rod to move and make each duct conversion valve to rotate, so that the intermediate case assembly is provided with an outer duct closing state and an outer duct opening state; in the outer duct closing state, each duct conversion valve is connected to the rear shunt ring in an overlap joint mode; and in the outer duct opening state, each duct conversion valve is separated from the rear shunt ring.
Owner:AECC SHENYANG ENGINE RES INST

Rotor wheel disk assembly structure

The invention belongs to the technical field of engine rotor wheel disk assembly design, and particularly relates to a rotor wheel disk assembly structure. The assembly structure comprises a primary rotor wheel disk, a plurality of connecting bolts, a plurality of clamping rings, a secondary rotor wheel disk and multiple connecting nuts, wherein the primary rotor wheel disk is provided with a primary drum, the primary drum is provided with a primary connecting edge, and the primary connecting edge is provided with a plurality of primary connecting holes formed in the circumferential direction;each connecting bolt correspondingly penetrate through one primary connecting hole, the head portions of the connecting bolts are located on the inner side of the primary drum, and annular clamping grooves are formed in the connecting bolts; each clamping ring is correspondingly clamped into one annular clamping groove; the secondary rotor wheel disk is provided with a plurality of secondary connecting holes in the circumferential direction; the portion, extending out of the corresponding primary connecting hole, of each connecting bolt correspondingly penetrates through one secondary connecting hole; each clamping ring is located between the primary connecting edge and the secondary rotor wheel disk; and each nut is correspondingly in threaded connection with one connecting bolt.
Owner:AECC SHENYANG ENGINE RES INST

Aero-engine nozzle adjusting mechanism

The invention belongs to the technical field of aero-engine nozzle adjusting mechanism design, and particularly relates to an aero-engine nozzle adjusting mechanism. The aero-engine nozzle adjusting mechanism comprises multiple rocker arms, pull rods, multiple actuating cylinders, a supporting ring and multiple connecting rod structures; the rocker arms are hinged to the outer wall of a nozzle connecting cylinder and distributed in the circumferential direction; one end of each pull rod is correspondingly hinged to one rocker arm, and the other end is correspondingly hinged to the outer wall of one convergence piece; a cylinder body of each actuating cylinder is hinged to the outer wall of the nozzle connecting cylinder; each piston rod is correspondingly hinged to one rocker arm to drive the corresponding rocker arm to rotate around the hinged part of the corresponding rocker arm and the nozzle connecting cylinder, so that the corresponding convergence piece is driven to move through the corresponding pull rod; the periphery of the nozzle connecting cylinder is sleeved with the supporting ring; one end of each connecting rod structure is hinged to the supporting ring, the other end is correspondingly hinged to the outer wall of one expansion piece, and the axial effective length can be adaptively adjusted in the process that the corresponding expansion piece moves along with the corresponding convergence piece.
Owner:AECC SHENYANG ENGINE RES INST

Intermediate case test load loading device

An intermediate case test load loading device comprises: an adapter cylinder, wherein one end of the adapter cylinder is in butt joint with an intermediate case, and the outer wall of the end is connected with a section torque loading connector and a section radial loading connector so as to apply section torque and radial load to the intermediate case; a switching frame connected with the end face of the other end of the switching cylinder, wherein two section bending moment and axial loading joints are connected to the switching frame so as to apply section bending moment and axial load to the intermediate case; a bearing frame connected to the switching frame, wherein a fulcrum axial load actuator is positioned and mounted on the bearing frame; a switching shaft, one end of the switching shaft is connected with a fulcrum part in the intermediate case, the other end of the switching shaft extends out of the switching cylinder, and the outer wall of the end is connected with a fulcrum radial loading joint so as to apply a fulcrum radial load to the intermediate case; and a switching rack arranged on the periphery of the switching shaft in a sleeving manner, connected with the fulcrum part in the intermediate case, ans connected with a fulcrum axial loading joint. The fulcrum axial loading joint is connected with the fulcrum axial load actuator so as to apply a fulcrum axial load to the intermediate case.
Owner:AECC SHENYANG ENGINE RES INST

Flexible vibration damping connection structure

The invention belongs to the technical field of flexible vibration damping connection design of a structure, and particularly relates to a flexible vibration damping connection structure. The flexiblevibration damping connection structure comprises a first supporting plate, a second supporting plate, multiple first supporting strips, multiple second supporting strips, multiple groups of first elastic pieces and multiple groups of second elastic pieces, wherein the second supporting plate is opposite to the first supporting plate; the multiple first supporting strips are arranged between the first supporting plate and the second supporting plate, and one end of each first supporting strip is connected with the first supporting plate; the multiple second supporting strips are arranged between the first supporting plate and the second supporting plate, one end of each second supporting strip is connected with the second supporting plate, and the second supporting strips and the first supporting strips are in cross distribution; each first elastic piece in each group of first elastic pieces is correspondingly arranged on the corresponding first supporting strip in the axial direction;each second elastic piece in each group of second elastic pieces is correspondingly arranged on the corresponding second supporting strip in the axial direction; and the elastic pieces on each firstsupporting strip are in cross distribution with the elastic pieces on the second supporting strip adjacent to the first supporting strip.
Owner:邱伊萍

Stator structure, rotor stator assembly structure with same and assembly method thereof

The invention belongs to the technical field of compressor assembly design, and particularly relates to a stator structure. The stator structure comprises a stator casing, two semi-annular edge rings,two semi-annular stator inner rings and two sets of stator blades. The inner wall of the stator casing is provided with an annular limit groove. The two semi-annular edge rings are arranged inside the stator casing and are butt each other to form an edge ring. One end of the edge ring is clamped into the annular limit groove. The two semi-annular stator inner rings are butt each other to form a stator inner ring. Each semi-annular stator inner ring is correspondingly arranged inside a semi-annular edge ring. Each set of the stator blades are arranged in a circumferential direction between thesemi-annular edge ring and the semi-annular stator inner ring corresponding to the semi-annular edge ring. The tip of each stator blade is formed on the inner wall of the corresponding semi-annular edge ring. A blade root is formed on the outer wall of the corresponding semi-annular stator inner ring. In addition, the invention also relates to a rotor stator assembly structure with the stator structure and an assembly method of a rotor stator structure.
Owner:AECC SHENYANG ENGINE RES INST
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