Electrostatic discharge prevention for a fan blade
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F04D-029/00
F04D-029/38
F01D-005/14
F01D-005/28
F01D-005/30
출원번호
US-0695178
(2015-04-24)
등록번호
US-10012238
(2018-07-03)
발명자
/ 주소
Robertson, Thomas J.
Hansen, James O.
Quinn, Mark
출원인 / 주소
UNITED TECHNOLOGIES CORPORATION
대리인 / 주소
Cantor Colburn LLP
인용정보
피인용 횟수 :
0인용 특허 :
6
초록▼
A fan blade capable of dissipating a buildup of electrostatic charge configured for operation within the fan assembly of a gas turbine engine. The fan blade has a fan blade body covered in a static dissipative coating. A conductive ground tab is attached to the front face of an airfoil root of the f
A fan blade capable of dissipating a buildup of electrostatic charge configured for operation within the fan assembly of a gas turbine engine. The fan blade has a fan blade body covered in a static dissipative coating. A conductive ground tab is attached to the front face of an airfoil root of the fan blade. Connected to the ground tab, a conductive flow path travels up the neck portion of the airfoil and along a lower portion of the fan blade. As static charge builds up on the fan blade, the electrostatic charge migrates down the fan blade and into the conductive flow path. Traveling along the conductive flow path the buildup of electrostatic charge accumulates on the conductive ground tab and exits the fan blade through contact with a disc rotor covering touching the conductive ground tab.
대표청구항▼
1. A fan blade capable of dissipating a buildup of electrostatic charge, the fan blade comprising: a fan blade body having a blade component, a fin platform, and an airfoil root having a first pressure face with a first runout traveling a length of the first pressure face and second pressure face wi
1. A fan blade capable of dissipating a buildup of electrostatic charge, the fan blade comprising: a fan blade body having a blade component, a fin platform, and an airfoil root having a first pressure face with a first runout traveling a length of the first pressure face and second pressure face with a second runout traveling a length of the second pressure face, the blade component of the fan blade body being covered in an electrostatic dissipative coating, wherein the fin platform protrudes outward on each side of the fan blade, and wherein a top side of the fin platform is covered in the static dissipative coating and an underside of the fin platform is not covered in the electrostatic dissipative coating;a conductive ground tab attached to a front face of the airfoil root;a conductive flow path attached to a top portion of the conductive ground tab and running along the airfoil root and the underside of the fin platform; anda wear covering enveloping a length of the first runout fillet of the first pressure face and a length of the second runout fillet of the second pressure face. 2. The fan blade according to claim 1, wherein the electrostatic dissipative coating is a urethane based coating. 3. The fan blade according to claim 1, wherein the conductive flow path is a conductive tape. 4. The fan blade according to claim 1, wherein the conductive flow path is a conductive sheet metal or a conductive foil. 5. The fan blade according to claim 1, wherein the conductive flow path is a conductive coating. 6. The fan blade according to claim 1, wherein the conductive flow path is a plurality of conductive ground wires. 7. The fan blade according to claim 6, wherein the plurality of conductive ground wires are secured to the top portion of the conductive ground tab by a weld, and the plurality of conductive ground wires run from the conductive ground tab up a neck portion of the airfoil root and along the underside of a fin platform of the fan blade body. 8. The fan blade according to claim 7, wherein the plurality of conductive ground wires are completely covered with an epoxy securing the plurality of conductive ground wires to the neck portion of the airfoil root and along the underside of the fin platform of the fan blade body. 9. The fan blade according to claim 1, wherein the conductive ground tab is attached in the middle of a front face of the airfoil root and secured to the front face of the airfoil root by an epoxy. 10. The fan blade according to claim 9, wherein the conductive ground tab is in contact with a disc rotor covering, the conductive ground tab being an end flow point of an accumulated electrostatic charge on the fan blade body and the accumulated electrostatic charge being transferred to the disc rotor covering through contact with the conductive ground tab. 11. A gas turbine engine, comprising: a fan having a plurality of fan blades connected to a rotor, the plurality of fan blades each having a fan blade body with a blade component, a fin platform, and an airfoil root having a first pressure face with a first runout traveling a length of the first pressure face and second pressure face with a second runout traveling a length of the second pressure face, the blade component of each of the plurality of fan blades being covered in an electrostatic dissipative coating, a conductive ground tab attached to a front face the airfoil root of each of the plurality of fan blades, a conductive flow path attached to a top portion of the conductive ground tab and running along the airfoil root and an underside of the fin platform; anda wear covering enveloping a length of the first runout fillet of the first pressure face and a length of the second runout fillet of the second pressure face,wherein the tin platform protrudes outward on each side of the fan blade, and wherein a top side of the fin platform is covered in the static dissipative coating and the underside of the fin platform is not covered in the electrostatic dissipative coating;a compressor downstream of the fan;a combustor downstream of the compressor; anda turbine downstream of the combustor. 12. The gas turbine engine according to claim 11, wherein the conductive flow path of each of the plurality of fan blades is a conductive tape. 13. The gas turbine engine according to claim 11, wherein the conductive flow path of each of the plurality of fan blades is a conductive sheet metal or a conductive foil. 14. The gas turbine engine according to claim 11, wherein the conductive flow path of each of the plurality of fan blades is a conductive coating. 15. The gas turbine engine according to claim 11, wherein the conductive flow path of each of the plurality of fan blades is a plurality of conductive ground wires. 16. The gas turbine engine according to claim 15, wherein the plurality of conductive ground wires of each of the plurality of fan blades are secured to the top portion of the conductive ground tab by a weld, and the plurality of conductive ground wires run from the conductive ground tab up a neck portion of the airfoil root and along an underside of a fin platform of the fan blade body for each of the plurality of fan blades. 17. The gas turbine engine according to claim 16, wherein the plurality of conductive ground wires of each of the plurality of fan blades are completely covered with an epoxy securing the plurality of conductive ground wires to the neck portion of the airfoil root and along the underside of the fin platform of the fan blade body on each of the plurality of fan blades. 18. The gas turbine engine according to claim 11, wherein the conductive ground tab of each of the plurality of fan blades is attached in the middle of a front face of the airfoil root and secured to the front face of the airfoil root by an epoxy. 19. The gas turbine engine according to claim 18, wherein the conductive ground tab of each of the plurality of fan blades is in contact with a disc rotor covering, the conductive ground tab being an end flow point of an accumulated electrostatic charge on the fan blade body and the accumulated electrostatic charge being transferred to the disc rotor covering through contact with the conductive ground tab on each of the plurality of fan blades. 20. A method of making a fan blade capable of dissipating a buildup of electrostatic charge for a gas turbine engine, the method comprising: machining a fan blade body to have a blade component, a fin platform, and an airfoil root having a first pressure face with a first runout traveling a length of the first pressure face and second pressure face with a second runout traveling a length of the second pressure face, wherein the fin platform protrudes outward on each side of the fan blade;covering the blade component of the fan blade body with an electrostatic dissipative coating, wherein a top side of the fin platform is covered in the static dissipative coating and an underside of the fin platform is not covered in the electrostatic dissipative coating;attaching a conductive ground tab to a front face of the airfoil root with an epoxy;attaching a conductive flow path to the conductive ground tab the conductive flow path traveling up a neck portion of the airfoil root and along the underside of the fin platform; andcovering the conductive flow path with an epoxy securely attaching the conductive flow path to each the neck portion of the airfoil root and the lower portion of the blade component of the fan blade body enveloping a length of the first runout fillet of the first pressure face and a length of the second runout fillet of the second pressure face in a wear covering.
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이 특허에 인용된 특허 (6)
Przytulski James C. (Fairfield OH) Hemsworth Martin C. (Cincinnati OH), Apparatus for preloading an airfoil blade in a gas turbine engine.
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