53results about How to "Improve abradability" patented technology

A enhanced abradable friable graded insulator FGI results from the laser patterning of a coating where a series of top surfaces reside on a series of columns such that the walls of the columns are not significantly densified relative to the interior of the columns. Patterns can be generated where the columns are oriented independently normal to or at an acute angle to the top surfaces. The cross sections of the top surfaces are formed to conform to the average dimensions of the spheres of the FGI coating. The cross sections of the top surfaces can be more than 1.5 times the diameter of the spheres. Various patterns of top surfaces can be used including regular, random, quasiperiodic patterns. A gradient of abradability can be imposed on the coating.

An air seal for use in a gas turbine engine provides improved durability, particularly at higher temperatures. The seal includes a seal substrate and an abradable seal layer on the substrate. The abradable seal layer is composed of a densified polyimide foam, preferably a thermomechanically densified foam. The seal is bonded to a stationary engine component such as a stator box or a case.

Turbine and compressor casing abradable components for turbine engines include abradable surfaces with a zonal system of forward (zone A) and rear or aft sections (zone B) surface features. The zone A surface profile comprises an array pattern of non-directional depression dimples, or upwardly projecting dimples, or both, in the abradable surface. The dimpled forward zone A surface features reduce surface solidity in a controlled manner, to help increase abradability during blade tip rubbing incidents, yet they provide sufficient material to resist incoming hot working fluid erosion of the abradable surface. In addition, the dimples provide generic forward section aerodynamic profiling to the abradable surface, compatible with different blade airfoil-camber profiles. The aft zone B surface features comprise an array pattern of ridges and grooves.

The invention provides a high temperature sealing coating and a making method thereof. The high temperature sealing coating comprises a sealing coating bottom layer and a sealing coating surface layer; the material of the sealing coating bottom layer is NiCoCrWMoSiB high temperature brazing alloy or NiCrCoSiB high temperature brazing alloy; and the material of the sealing coating surface layer comprises 5-12wt% of polyphenyl ester, 5-10wt% BaF2/CaF2, and the balance of NiCrAlYSi alloy or NiCrAlY alloy or NiCoCrAlTaY alloy or CoCrAlY alloy. The making method of the high temperature sealing coating comprises the following steps: making the sealing coating bottom layer on a substrate through cold gas dynamic spraying; making the sealing coating surface layer through plasma spraying; carrying out heat insulation on the substrate sprayed with the high temperature sealing coating at 500DEG C to obtain a pre-product; and carrying out vacuum diffusion treatment on the pre-product at 1150-1250DEG C for 15-30min to complete the production of the high temperature sealing coating. The high temperature sealing coating has the characteristics of low hardness, self lubrication, low friction coefficient and long life, can work at a temperature of 1150DEG C, and can be used for sealing gas paths of aeroengines and ground gas turbine high pressure turbines.

The invention relates to a multi-components hot spray flexible wire and a preparation method thereof. A flexible wire which is good in spraying technology adaptability is prepared through a method of mechanical milling, rubber mixing and squeezing by a slow vernier hydraulic press. The wire comprises Ni, Al, Cr, W, Co, Mo, Ti, Cu, C, BN and Si oxide or salts thereof, wherein the raw materials can be simple substance powder or alloy or compound, while the oxides can be one or more or the combination of a few materials. The binder can be inorganic materials, and the combination of some additives and addition agents is also included. The coating prepared by the wire has the advantages that the coating combines well with a matrix, the wearable performance is good, and the thermal shock resistance and salt-fog resistance are excellent. The wire has a wide application range, which can be applied in the surface modification and the reproduction of mechanical equipment.

The invention relates to a wearable seal coating material, in particular to a cyclic silicon resin seal coating used for an industrial centrifugal compressor. The cyclic silicon resin seal coating comprises the following components in percentage by weight: 65-80% of cyclic silicon resin, 15-25% of filling material A and 5-10% of filling material B, wherein the filling material A is one or more than two of polyether ether ketone, polybenzoate and polytetrafluoroethylene, and the granularity is 50-100 microns; when more than two of polyether ether ketone, polybenzoate and polytetrafluoroethylene are mixed, the mixing ratio can be an any ratio; the filling material B is one or more than two of hexagonal boron nitride, graphite and bentonite, and the granularity is 20-50 microns; and when more than two of hexagonal boron nitride, graphite and bentonite are mixed, the mixing ratio can an any ratio. The invention effectively increases the scraping property of the coating, can control and regulate the hardness of the coating and has self lubricating property so that the hardness of the coating can reach the range applicable to scraping, the abrasion of vanes is reduced, the wearable property of the coating is increased, and the invention can ensure that contact wearing can not endanger a rotor.

Provided is a gas turbine that can solve a problem in which a seal fin of a turbine blade is abraded by a brazed place of a honeycomb seal.

A gas turbine 100 includes a compressor 10, a combustor 20, and a turbine 30. The turbine 30 includes: a honeycomb seal 7 disposed so as to be secured to a casing side in a clearance between the casing 1 and turbine blades 5A-5C rotating around a rotating shaft 4 extending in a longitudinal direction of the casing 1 and a seal fin 6 provided on an end face of each of the turbine blades 5A-5C facing the honeycomb seal 7, the seal fin 6 extending in a direction perpendicular to the rotating shaft 4. The honeycomb seal 7 is formed by a plurality of corrugated thin sheet metals 71 overlapped with each other at walls of node 71a thereof and the walls of node 71 blazed with each other, each of the corrugated thin sheet metals 71 having trapezoids alternately continued. A longer direction (Y1 direction) of the wall of node 71a of the honeycomb seal 7 is tilted with respect to the rotational direction (Z direction) of the turbine blades 5A-5C.

The invention provides a turbine moving blade with bevelled prism cavities formed in a blade top. The turbine moving blade comprises a blade body, the multiple bevelled prism-shaped cavities are formed in the blade top of the blade body from the front edge to the tail edge, the bottom faces of the prism-shaped cavities adopt a bevelled mode, the ratio of the maximum height of the prism-shaped cavities to the height of the blade body is 0.5%-4%, and the beveled angles for beveling the bottom faces of the prism-shaped cavities are within the range of 30-60 degrees. According to the turbine moving blade with the bevelled prism cavities formed in the blade top, a part of leakage fluid entering a gap enters the prism-shaped cavities to be curled up to form vortexes, on the one hand, kinetic energy of the gap fluid is dissipated, on the other hand, the jet blocking effect on the gap fluid above the cavities is formed, then the purpose of controlling blade tip leakage flow of a turbine is achieved, the bottom faces of the prism cavities are beveled, the vortex intensity and development direction of the vortexes in the cavities are changed, the mixing effect of the fluid flowing into/flowing out of the cavities and the fluid in the gaps on the upper portion is enhanced, inhibiting turbine blade tip leakage flow is more advantageous, and the structure is simple.

Provided is a versatile heat-curable resin composition for semiconductor encapsulation that has a favorable water resistance and abradability, and exhibits a superior fluidity and a small degree of warpage even when used to perform encapsulation on a large-size wafer.

The heat-curable resin composition of the invention contains:

• (A) a cyanate ester compound having not less than two cyanato groups in one molecule;
• (B) a phenol curing agent containing a resorcinol-type phenolic resin;
• (C) a curing accelerator; and
• (D) a spherical inorganic filler.