14 results about "Foreign object damage" patented technology

The application provides a foreign object damage pre-preparation system and method in a blade rotating state, the system comprising: a tester cavity, in a vacuum state during a test; a motor for driving the tester to rotate; a driving shaft connecting the motor and a test piece mounting disc; the test piece mounting disc for bearing a blade test piece, the blade test piece being mounted on the edge of the test piece mounting disc; a counterweight mounted on the test piece mounting disc for a counterweight sensor for the blade test piece, the sensor extending into the tester cavity for measuring the rotating speed of the blade test piece; a controller connecting the motor, the sensor and a projectile launcher, the projectile launcher comprising a barrel, and a projectile being mounted in the barrel. The controller controls the projectile projection trigger time, so that the projectile freely falls down and hits the leading edge position of the blade requiring foreign object damage pre-preparation, thereby realizing foreign object damage pre-preparation.

The application provides an aero-engine blade fatigue failure analysis method, first, the foreign object damage morphology data of the real blade is collected to form a real blade database, then the design parameters of the simulation blade are obtained according to the morphology and stress distribution of the real blade, and then the finite element model of the simulation blade is established, the modal calculation is carried out, whether the inherent frequency of each order mode meets the set requirement is verified, if the set requirement is met, the foreign object damage simulation of the finite element model of the simulation blade is carried out, the simulation result is obtained, and the consistency verification is carried out with the real blade database, finally, the real model of the simulation blade is made, the FOD test and the HCF test are continuously carried out on the real model of the simulation blade, and the fatigue limit of the real model of the simulation blade after damage is obtained. The method takes the foreign object damage morphology data of the real blade as the reference, realizes the high-cycle fatigue limit test of the foreign object damage simulation blade which is closer to the real working condition, has low cost, high controllability of parameters, and good interpretability.

The utility model relates to a planetary extruder, and relates to the field of planetary extruders. The device comprises an extruder body, a feeding shell is fixedly installed above the extruder body, a positioning frame is installed in the feeding shell, the positioning frame and the feeding shell are clamped and fixed, a cleaning rotary frame is installed at the lower end of the positioning frame, and a motor for driving the cleaning rotary frame to rotate is installed on the upper end face of the positioning frame; a feeding shell is further installed on the upper end face of the feeding shell. By arranging the cleaning swing frame, raw materials remaining in the feeding shell can be cleaned in time, the feeding blockage problem caused by raw material accumulation is avoided, the feeding smoothness of the planetary extruder is guaranteed, and the production efficiency is improved. The protective blocking frame can effectively prevent foreign matter from entering the feeding shell, and the risk that equipment is damaged by the foreign matter is reduced.

A method of monitoring operation of an aircraft engine includes, during operation of the aircraft engine, monitoring a parameter associated with the aircraft engine using one or more sensors. In response to determining that one or more values of the parameter are indicative of a foreign object damage (FOD) event of a first severity level to the aircraft engine, communicating data pertaining to the FOD event of the first severity level in accordance with a first communication scheme assigned to the first severity level. In response to determining that one or more values of the parameter are indicative of FOD event of a second severity level to the aircraft engine, the second severity level being higher than the first severity level, communicating data pertaining to the FOD event of the second severity level in accordance with a second communication scheme assigned to the second severity level.

The application provides an aero-engine blade vulnerable area division method, system, device and storage medium. First, numerical models of various real aero-engine blades are established, modal analysis is performed by using finite element analysis software, the sizes of leading edge cross sections under the first three modes are compared, and a numerical model with a thinner cross section is selected and marked as a dangerous numerical model. Then, a dangerous mode of the dangerous numerical model is selected according to the dynamic stress test result, and the position of the corresponding maximum stress point under the dangerous mode is the vulnerable area of the corresponding real blade. The above division method can find the weak parts of the blade vulnerable to damage before the foreign object damage experiment, has good operability and good interpretability, accelerates the experimental process, and greatly reduces the cost of the experiment.

A protective cover for foreign object damage prevention is disclosed, including a polyurethane foam body dimensioned to be at least partially received by an inlet and an exhaust of an aircraft. One or more handles are at least partially embedded into a front side of the foam body to enable input and removal of the foam body to and from the inlet. The protective cover protects the aircraft from foreign object damage caused by the ingestion and impact of foreign object debris.

A protective cover for foreign object damage prevention is disclosed, including a polyurethane foam body dimensioned to be at least partially received by an inlet and an exhaust of an aircraft. One or more handles are at least partially embedded into a front side of the foam body to enable input and removal of the foam body to and from the inlet. The protective cover protects the aircraft from foreign object damage caused by the ingestion and impact of foreign object debris.

The utility model provides a protective screen window which comprises a window frame, a gauze element, a protective assembly and a containing device, and the unfolded area of the gauze element at least covers a frame body of the window frame; the protection assembly is connected with the gauze element and extends from one side of the window frame to the other side of the window frame. The containing device is located on one side of the window frame, a containing space is formed in the containing device, and at least part of the gauze element and the protection assembly can be contained in the containing space. According to the protective screen window provided by the utility model, the protective component is arranged on the gauze element, so that the gauze element can bear larger impact force, and the protective component and the gauze element are difficult to damage even if the gauze element is damaged by external foreign matters, so that the gauze element can not be damaged even if the gauze element is accidentally impacted by an indoor child when the child plays the protective screen window. And the safety of indoor children can still be protected to the greatest extent.

A system configured to reduce foreign object damage to an asset during an industrial operation is disclosed herein. The system can include a substrate. The substrate can define a plurality of designated locations. The system can further include a plurality of protective barriers. Each protective barrier of the plurality of protective barriers can be configured for installation on a different portion of the asset and is configured to protect the asset during the industrial operation when installed on the different portion of the asset. Each protective barrier of the plurality of protective barriers can be further configured for reinstallation into a geometrically corresponding location of the plurality of designated locations of the substrate.

The invention relates to a method for reducing foreign matter damage caused by rotation of a valve element and a valve body.The method comprises the following steps that sealing structures are rotationally arranged in an inlet and an outlet of a shell of the valve element, and the sealing structures are in sealing fit with the valve element and can freely rotate in the inlet and the outlet; a transmission structure is arranged between the valve element and the sealing structure and can push the sealing structure to rotate when the valve element rotates. According to the technical scheme, when the valve element rotates, the transmission structure drives the sealing structure to rotate in the inlet or the outlet, when the valve element rotates and extrudes sundries, the sealing structure rotates to take the sundries away from the contact face, in other words, the sealing structure unloads force through rotation, support to the sundries is relieved, and the sealing effect is improved. And damage of foreign matters to the sealing structure in the rotating process of the valve element is reduced.

The application belongs to the technical field of blade foreign object damage test, and provides an aero-engine blade foreign object damage test device, a test method and a processing method, wherein the device comprises an outer casing, an inner casing and a blade disc; the inner casing is installed in the inner casing; an airflow channel is formed between the outer casing and the inner casing; the blade disc is located outside the inner casing and is installed on the surface of a driving shaft; the blade disc is pre-fabricated with a notch for simulating an engine blade with damage; the present application takes the blade disc with a notch as a test object to simulate the working condition of the engine blade with damage on the engine; through the above setting, the foreign object damage test of the whole machine state can be simulated at a lower test cost, the foreign object damage test working condition of the engine blade is restored, and the damage of the whole engine caused by test failure is avoided.

A method for improving the foreign object damage tolerance of a ceramic matrix composite (CMC) structures by applying an environmental barrier coating (EBC) containing an intumescent material to the surface of the ceramic matrix composite. The EBC coated ceramic matrix composite is heated to intumescent material expansion temperature of, for example, between about 600 to 1000° C. to expand the intumescent material. The intumescent loaded EBC layer may be applied to a CMC that does or does not contain intumescent material.

A method of monitoring operation of an aircraft engine includes, during operation of the aircraft engine, monitoring a vibration parameter associated with the aircraft engine and monitoring a performance parameter associated with the aircraft engine. In response to determining that one or more values of one of the vibration parameter and the performance parameter are indicative of foreign object damage (FOD) to the aircraft engine, determining whether one or more values of the other one of the vibration parameter and the performance parameter are indicative of FOD to the aircraft engine. In response to determining that the one or more values of both the vibration parameter and the performance parameter are indicative of FOD to the aircraft engine, registering a confirmed occurrence of FOD to the aircraft engine in a non-transitory memory associated with the aircraft engine.

The invention belongs to the technical field of titanium alloy preparation, and particularly discloses a foreign object damage resistance enhanced titanium alloy and a preparation method thereof.The foreign object damage resistance enhanced titanium alloy is prepared from, by mass, 4.5%-5.0% of Al, 5.5%-7.0% of the total amount of Mo and Cr, 5.0%-7.0% of the total amount of Sn and Zr and the balance Ti; titanium powder and the intermediate alloy powder are mixed to obtain mixed powder; performing cold isostatic pressing on the mixed powder to obtain a green body, and performing vacuum sintering on the green body to obtain a sintered ingot; the sintered ingot is subjected to hot isostatic pressing treatment, and a hot isostatic pressing ingot is obtained; the hot isostatic pressing ingot is pre-forged, and a powder metallurgy forged sample is obtained; and the powder metallurgy forged sample is subjected to heat treatment, and the titanium alloy component is obtained. According to the method, the alloy components are adjusted, the content of beta stable elements is optimized, and the dynamic impact performance and damage tolerance of the titanium alloy material are improved.