Patent Document

This invention was made with Government support under Contract Number N00019-02C-3003. The Government has certain rights in this invention. 
    
    
     BACKGROUND OF THE INVENTION 
     1. Field of the Invention 
     The present invention is related to a flexible heater assembly for an aerospace component. More particularly, the present invention relates to flexible heater assembly for an aerospace component that includes erosion protection and erosion indication in an aerodynamic and ingestion resistant optimized assembly. 
     2. Description of Related Art 
     The operating environment of aerospace components, particularly, gas turbine engine components is exceedingly harsh and demanding. The temperatures and liquid water content that the components are exposed to in the path of the air stream through the engine can result is ice accretion. In such environments electro-thermal ice protection systems are needed to protect the engine components from damage caused by ingestion of accreted ice pieces. 
     Present surface mounted applications to protect gas turbine engine components have drawbacks. The machinable silicone rubbers presently used for such purposes suffer from high erosion. Further, current surface mounted heaters are non-structural and occupy valuable space in the jet turbine engine that is optimally reserved for structural components that would ensure greater structural strength and aerodynamic performance of the engine. Additionally, silicone elastomers with improved erosion resistance used for surface mounted applications are highly detrimental to the life of the rotating jet turbine blades in the event that the adhesive that secures the heater element to the engine component fails. Still further, electrical injuries are a concern for maintenance personnel from hard particle erosion or localized damage, because removal of the silicone layer over the heating element does not cause electrical failure although components are electrically active. 
     Accordingly there is a need for an surface mounted flexible heater for gas turbine engine applications that offers high erosion resistance, minimum reduction of component structural strength and aerodynamic performance while minimizing its ingestion risk and potential mechanical failure. 
     SUMMARY OF THE INVENTION 
     It is an object of the present invention to provide a surface mounted heater assembly for a gas turbine engine component that provides erosion protection and erosion indication together with a readily gas turbine machinable polymer support and adhesive. 
     It is another object of the present invention to provide a surface mounted heater assembly for a gas turbine engine component that provides high erosion protection with minimized ingestion risk. 
     It is also an object of the present invention to provide a surface mounted heater assembly for an engine component that is capable of abrading during engine operation to prevent mechanical damage to rotating gas turbine engine blades. 
     It is a yet another object of the present invention to provide a surface mounted heater assembly for a gas turbine engine component that minimizes the overall thickness of the assembly and protects against erosion and minimizes ingestion risk. 
     It is yet still another object of the present invention to provide a surface mounted gas turbine engine heater assembly for an component that employs both erosion resistance and erosion indication to enable detection of potential electrical malfunction. 
     It is still yet another object of the present invention to provide a surface mounted heater assembly for a gas turbine engine component that employs a transition layer between a machinable adhesive when used with a co-molded composite structure. 
     It is still yet another object of the present invention to provide a surface mounted heater assembly for a gas turbine engine component that employs a transition layer between a machinable adhesive and a co-molded composite structure that is a structural component. 
     These and other objects and advantages are provided by a surface mounted heater assembly for an aerospace component having a support layer, an electrically resistive heater foil element supported by the support layer, a coating covering the heater element; and an adhesive to secure said support layer to the component. The coating has two layers that are visually distinct to permit identification of potential exposure of said heater foil element. A surface mounted heater for an aerospace component having a multiple layer assembly having a support layer; a heater element supported by the support layer and a protective coating covering the heater element. The multiple layer assembly further comprises a transition layer to couple the support layer to the aerospace component. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
       These and other features and advantages of the present disclosure will be appreciated and understood by those skilled in the art from the following detailed description, drawings, and appended claims. 
         FIG. 1  illustrates a gas turbine engine air foil having a conventional surface mounted heater shown in detail; 
         FIG. 2  illustrates a gas turbine engine air foil having a surface mounted heater shown in detail according to a first embodiment of the present invention; and 
         FIG. 3  illustrates a gas turbine engine air foil having a surface mounted heater shown in detail according to a second embodiment of the present invention. 
     
    
    
     DETAILED DESCRIPTION OF THE INVENTION 
     Referring to the drawings and in particular to  FIG. 1 , a conventional surface mounted heater assembly for a gas turbine engine air foil component is shown in detail, generally represented by reference numeral  10 . Heater assembly  10  is affixed to a air foil  15  by an adhesive layer  20 . Adhesive layer  20  connects the air foil to heater assembly  10 . The upper most gas flow contacting layer is a silicone cover layer  25 . Cover layer  25  protects heater element  30 . Heater element  30  is supported by silicone support  35 . Air foil  15  is part of a larger gas turbine engine component, such as for example a gas turbine engine air foil vane component  40 . 
     Traditionally, heater element  30  is an electrically resistive metal foil of a material such as titanium, a titanium alloy, a copper alloy, nickel or nickel alloys. The entire heater assembly  10  is a flexible surface mounted assembly typically consisting of a copper or nickel alloy heater element, a calendered silicone support reinforced with a glass scrim cloth incorporated during the calendaring process and a calendered silicone cover layer. Heater element  30  is then bonded to air foil  15  using adhesive  20  commonly used for such applications. Primers may be used to increase the adhesion. Assembly  10  has a thickness of approximately 0.002-0.005 inch. 
     Numerous disadvantages exist with this conventional configuration that uses a silicone rubber for cover layer  25  that is not very erosion resistant. Accordingly, a relatively thick layer of silicone rubber is required at a minimum thickness of 0.010 to 0.020 inch to achieve sufficient gas turbine component erosion durability. Further, the entire surface mounted heater assembly  10  is relatively thick. The entire surface mounted heater assembly  10  including cover layer  25 , the heater element  30 , support layer  35  and adhesive  20  is about 0.030-0.060 inch thick. In the relatively, confined space of the turbine engine, such a thickness occupies volume that could be used for structural load bearing components of the engine. Accordingly, engines that must use a thick heater assembly such as the conventional configuration, compromise structurally integrity and aerodynamic performance. 
     Additionally, silicone elastomers with improved erosion resistance used for surface mounted applications are highly detrimental to the life of the rotating jet turbine blades in the event that adhesive  20  that secures the heater element to the engine component fails. Any liberation of the heater assembly into the rotating jet turbine blades could completely destroy or substantially reduce the performance of the engine. 
     Still further, electrical injuries are a concern for maintenance personnel when the cover layer is removed by hard particle erosion or localized damage. In conventional heater assembly  10 , the removal of the silicone layer over the heating element may not cause electrical failure and components remain electrically active without sufficient electrical insulation. Such a scenario poses hazards to the maintenance personnel. 
     Referring the  FIG. 2 , the first embodiment of the heater assembly of the instant invention, generally referred to by reference numeral  50 , is shown. Heater assembly  50  is affixed to a gas turbine engine component such as an air foil  55  that is in the gas path. Heater assembly  50  has two layers, or a protective coating, directed to erosion resistance of heater assembly  50 , erosion protection layer  60  and erosion indicator layer  65 . Immediately beneath protective layers  60  and  65 , is heater element  70 . Heater element  70 , such as an electrically resistive layer, is directly between erosion indicator layer  65  and gas turbine machinable support layer  75 . Support layer  75  is affixed to air foil  55  by a turbine machinable adhesive  80 . Heater assembly  50  is shown as being affixed to air foil  55  of a gas turbine engine stage  85 ; however, the heater assembly  50  of the instant invention could be affixed to any aerospace component, especially those components that are subjected to the gas turbine engine gas path. 
     Erosion protector layer  60  is immediately adjacent the gas flow and is preferably a polymer layer that is erosion resistant. Fluorocarbon elastomers are preferably used on the heater assembly surface because they offer erosion protection to the underlying heater element  70  and air foil  55 . Erosion protection layer  60  is preferably formed from a solvated elastomer formulated for erosion resistance and is preferably approximately equal to or greater than 0.005 inch thick. For example, PLV2100 solution, a product of Pelseal Corporation, is capable of providing erosion resistance. Layer  60  is applied by conventional techniques such as spraying, electrostatic spraying, roll coating and powder coating to achieve sufficient adhesion to the erosion indicator layer  65  and  6  control the thickness. Primers applied per manufacturers instructions may be used to achieve sufficient adhesion. 
     Erosion indicator layer  65  is preferably an erosion resistant polymer layer that is inherently a different color than erosion protector layer  60 . Alternatively, erosion indicator layer  60  has an additional electrically non-conductive chemical compound added to modify its color when inspected with electromagnetic radiation such as visible light, ultraviolet or infrared light to enable viewing. In any case, erosion indicator layer  65  is visually distinct from erosion protector layer  60  to ensure detection of any defect in erosion protector layer  60  that could lead to injury of personnel. Were erosion indicator  65  not present, hard particle erosion or localized damage due to impacts would remove the polymer surface covering the heating element without causing an electrical failure, as in the conventional flexible heater silicone coatings. Without electrical failure, the heater assembly diagnostics could not detect the damage resulting from an electrically active jet turbine component surface that could harm maintenance personnel. 
     Erosion indicator layer  65  is also applied by any conventional means such as spraying, electrostatic spraying, roll coating and powder coating techniques. The thickness of erosion indicator layer  65  is approximately from 0.0005-0.005, and more narrowly, 0.0005-0.001 inch to achieve sufficient adhesion to erosion protector layer  60  and heater element  70 . Primers applied per manufacturers instructions may be used to achieve sufficient adhesion. Additionally sufficient erosion indicator layer  65  is applied to provide electrical isolation from personnel at the heater operational voltage and wattage. This combination of erosion protection layer  60  and erosion indicator layer  65  provide needed erosion resistance in the gas turbine engine gas path lengthening the service life of the air foil. 
     Heater element  70  is an electrically resistive foil metal heater element that is preferably made from a material such as but not limited to titanium, titanium alloys, copper alloys, nickel and nickel alloys. Heater element surface is prepared for bonding using chemical etches, plasma etches and primers appropriate to the heater element  70  alloy. Heater element  70  has a thickness of approximately 0.0005-0.005 inch. 
     Heater element  70  is connected to a support layer  75 . Support layer  75  is preferably a polymer layer that supports heater element  70  during processing. Support layer  75  is of sufficient strength to withstand service under engine operating conditions. However, support layer  75  must also be machinable by the turbine blades if ingested to minimize or eliminate engine damage should it become separated from air foil  55 . Support layer  75  is preferably made from a polymer that supports heater element  70  during chemical milling operations. The support layer  75  can be a polymer film or calendered sheet applied by conventional autoclave or compression molding methods. Support layer  75  can be polymer powder applied by conventional methods such as powder coating. Support layer  75  can be polymer film formed by evaporation of a solution applied by conventional methods such as spraying, electrostatic spraying, and roll coating. Preferably, all forms are applied at a thickness sufficient to support the heater element  70  during chemical milling operations and achieve sufficient adhesion to adjacent materials typically 0.001 inch to 0.010 inch. Primers applied per manufacturers instructions may be used to achieve sufficient adhesion. 
     Machinable adhesive  80  secures heater assembly  50  to engine component  55 . Machinable adhesive  80  is preferably a polymer adhesive that bonds the support layer  75  to air foil  55  with sufficient strength for durable service under the operating conditions of the jet air stream. Accordingly, a polymer that is durable yet machinable by the turbine blades is used to minimize or eliminate engine damage during potential ingestion. The machinable adhesive  80  can be a calendered sheet applied by conventional autoclave or compression molding methods. Machinable adhesive  80  can be a polymer film formed by evaporation of a solution applied by conventional methods such as spraying, electrostatic spraying, and roll coating. Machinable adhesive  80  can be a polymer powder applied by conventional means such as powder coating techniques. Preferably, all forms are applied at a thickness of typically 0.0005 inches to 0.010 inches. Primers applied per manufacturers instructions may be used to achieve sufficient adhesion. The overall thickness of the heater assembly  50  is approximately 0.007 inches to 0.035 inches; although, the upper limit is determined by the amount of space available. 
     The heater assembly  50  of the first embodiment is intended for applications where the gas turbine engine air foil  55  or other component is a fiber reinforced polymer, metal or ceramic matrix composite or a fabricated metal structure. To affix heater assembly  50  to air foil  55 , support layer  75 , for example a fluorocarbon solution, is spray applied to a 0.001 inch thick CP titanium foil heater  70 . Support layer  75  is then cured to provide the support required for chemical milling of the heater element  50 . The thickness of support layer  75  is approximately from 0.001 to 0.010 inch. 
     After being chemically milled, exposed heater element  50  is spray coated with an approximately 0.001 inch thick layer of erosion indicator layer  65  and then erosion protector layer  60 . The outermost erosion protector layer  60  is approximately 0.009 inch in thickness. Layers  60  and  65  are thermally cured. Machinable adhesive  80  is then preferably spray coated to support layer  75  at a thickness of approximately 0.004 inch. The uncured adhesive  80  is laid onto air foil  55  and thermally cured using externally applied pressure, temperature and vacuum. Alternative methods for applying the flexible surface mounted heater assembly  50  could alternatively be used. 
     The overall thickness of the heater assembly  50  of the first embodiment is approximately 0.007 inch to 0.035 inch. The upper limit is determined by the amount of space available. The overall thickness of the convention heater  9  assembly for gas turbine components has a thickness range of 0.030 to 0.060 inch. The benefit of reduced thickness is highly significant in the confined regions within the gas turbine engine. Reduced thickness, permits greater structural support for the turbine and increased aerodynamic performance. Furthermore, the combination of erosion protector  60  and erosion indicator  65  in the path of the air stream result in extended service life of the gas turbine component. Erosion indicator  65  permits easy inspection for erosion for damage while increasing safety for maintenance personnel. The materials used for the polymer support layer  75  reduce turbine damage during potential ingestion. 
     Referring to  FIG. 3 , a second embodiment of heater assembly generally resented by reference numeral  100 , is shown. Heater assembly  100  incorporates elements  105  erosion protector layer, erosion indicator layer  110 , heater element  115  and machinable support  120  layer, similar to first embodiment. Heater assembly  100  further includes a transition layer  125 . Transition layer  125  is required when heater assembly  100  is co-molded during fabrication of a polymer matrix composite gas turbine component such as an air foil  130  or secondarily attached with a conventional thermoset adhesive. 
     Transition layer  125  is preferably a fabric layer such as a glass fabric layer that is coated on one side adjacent to the machinable support layer  120  with a machinable adhesive. The machinable adhesive amount is sufficient to adhesively attach the transition layer to the heater assembly. Additionally the transition layer retains sufficient fabric volume to allow partial impregnation of the transition layer with the adhesive or composite matrix resin during the heater attachment procedures. The second side of transition layer  125 , proximate gas turbine component is secondarily attached using thermoset polymers such as polyurethane, epoxy, bismaleimide, phthalonitrile or polyimide or co-molded with a thermoset composite structure such as epoxy, phthalonitrile, polyimide or bismaleimide reinforced with graphite or ceramic fibers. The composition and bismaleimide reinforced with graphite or ceramic fibers. The composition and thickness of transition layer  125  is approximately 0.004 inch and contributes to the structural requirements of the gas turbine engine component. Additionally the transition layer can be integrated into the support layer. 
     In the second embodiment, support layer  120  is applied by spraying heater element  115  and then curing the support layer  120  in preparation for further chemical milling. Support layer  120  is preferably sprayed to heater element  115  at a layer of approximately 0.005 inch. The heater element  115  is preferably CP titanium and has a thickness of approximately 0.001 inch. 
     After being chemically milled, exposed heater element  115  is spray coated with an approximately 0.001 inch thick layer of erosion indicator layer  110  and then erosion protector layer  105 . The outermost erosion protector layer  105  is approximately 0.005 inch to 0.020 inch in thickness, although the upper limit of the range is determined by the amount of space available. Layers  105  and  110  are thermally cured. 
     Transition layer  125  is spray coated, powder coated or roll coated with machinable adhesive at a thickness of approximately 0.0001 inch to 0.005 inch. Transition layer  125  is bonded to support surface of heater assembly  100 . For a dry assembly process such as resin transfer molding the assembly is stacked with the composite component fabric and fabricated using appropriate tooling and processes. Alternatively, the co-molding process could involve a pre-impregnated process such as autoclave or compression molding. 
     The benefits of the heater assembly  100  of the second embodiment in comparison to the conventional are identical. Further, the co-molded heater assembly  100  of the second embodiment reduces costs in comparison to the conventional heater assembly by eliminating operations associated with secondarily bonding such as mechanically abrading, solvent cleaning and priming. Further the transitional layer having a thickness of 0.004 inch contributes to the composite structure, thus providing a load bearing element. Additionally, the fluorocarbon erosion indicator and erosion protection layer eliminate the bonding contamination typically introduced by the use of silicones. 
     While the instant disclosure has been described with reference to one or more exemplary embodiments, it will be understood by those skilled in the art that various changes may be made and equivalents may be substituted for elements thereof without departing from the scope thereof. In addition, many modifications may be made to adapt a particular situation or material to the teachings of the disclosure without departing from the scope thereof. Therefore, it is intended that the disclosure not be limited to the particular embodiment(s) disclosed as the best mode contemplated for carrying out this invention, but that the disclosure will include all embodiments falling within the scope of the appended claims.

Technology Category: 2