Hybrid turbine blade including multiple insert sections
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F01D-005/14
F01D-005/28
F04D-029/32
F04D-029/02
출원번호
US-0774581
(2013-02-22)
등록번호
US-9309772
(2016-04-12)
발명자
/ 주소
Spoonire, Ross Ashely
Lin, Wendy Wen-Ling
Schilling, Jan Christopher
Shim, Dong Jin
Gemeinhardt, Gregory Carl
Jadhav, Prakash Kashiram
출원인 / 주소
General Electric Company
대리인 / 주소
Darling, John P.
인용정보
피인용 횟수 :
0인용 특허 :
8
초록▼
A hybrid turbine blade and method of fabrication, comprising a shank portion and an airfoil portion. The airfoil portion comprising a composite outer structure having a recess formed therein and an alternating stack of at least one composite section and at least two insert sections disposed in the r
A hybrid turbine blade and method of fabrication, comprising a shank portion and an airfoil portion. The airfoil portion comprising a composite outer structure having a recess formed therein and an alternating stack of at least one composite section and at least two insert sections disposed in the recess. The outer composite structure and the at least one composite section having a first density. The at least two insert sections having a second mass density, which is less than the first mass density. The composite outer structure and the alternating stack of at least one composite section and at least two insert sections together define an airfoil portion that meets all mechanical load carrying requirements of said hybrid turbine blade such that no load transfer needs to occur through said at least two insert sections.
대표청구항▼
1. A hybrid turbine blade comprising: a shank portion; andan airfoil portion including an outer composite structure and having a recess formed therein, the airfoil portion comprising:at least one composite section having a first density;at least two insert sections each having a second mass density
1. A hybrid turbine blade comprising: a shank portion; andan airfoil portion including an outer composite structure and having a recess formed therein, the airfoil portion comprising:at least one composite section having a first density;at least two insert sections each having a second mass density which is less than said first mass density, the at least two insert sections disposed in alternating laminate stacked relationship with the at least one composite section and defining an alternating laminate stack of the at least one composite section and the at least two insert sections,wherein the alternating laminate stack of the at least one composite section and the at least two insert sections is disposed in the recess and having a major axis extending along a span of the airfoil portion, a minor axis extending along a chord of the airfoil portion and a thickness extending perpendicular to the major axis and through a thickness of the airfoil portion,wherein an outermost layer of the at least two insert sections is bonded to the outer composite structure, andwherein said outer composite structure, said alternating laminate stack of the at least one composite section and said at least two insert sections together define an airfoil shape. 2. The hybrid turbine blade of claim 1, wherein said at least two insert sections have a stiffness and dimensional stability to maintain said airfoil shape, and wherein said at least two insert sections retain compliance and flexibility to conform to said recess. 3. The hybrid turbine blade of claim 1, wherein said at least one composite section is comprised of a plurality of composite material layers comprising fiber filaments embedded in a matrix binder. 4. The hybrid turbine blade of claim 3, wherein said at least one composite section is comprised of graphite fibers embedded in an epoxy resin matrix binder. 5. The hybrid turbine blade of claim 1 wherein: said airfoil portion has a design operating temperature and further comprises a blade root attached to said shank portion, a blade tip, and a radial axis extending outward toward said blade tip and inward toward said blade root, and wherein said alternating laminate stack of the at least one composite section and the at least two insert sections substantially extends from said blade root to said blade tip. 6. The hybrid turbine blade of claim 5, wherein said at least two insert sections maintain dimensional stability at said design operating temperature. 7. The hybrid turbine blade of claim 1 further comprising an erosion coating disposed on and bonded to at least a portion of a pressure side and at least a portion of a suction side of said outer composite structure. 8. The hybrid turbine blade of claim 1, wherein said first mass density has a range from 1.4 grams per cubic centimeter to 2.0 grams per cubic centimeter. 9. The hybrid turbine blade of claim 1, wherein said second mass density has a range from 0.01 grams per cubic centimeter to 0.9 grams per cubic centimeter. 10. The hybrid turbine blade of claim 1, wherein said composite outer structure has a first volume and said alternating laminate stack of the at least one composite section and the at least two insert sections has a second volume, and wherein said second volume has a value corresponding to at least ten percent of said first volume. 11. The hybrid turbine blade of claim 1, wherein a thickness of the at least one composite section is on an order of magnitude of a thickness of each of said at least two insert sections. 12. The hybrid turbine blade of claim 1, wherein an insert termination of each the at least two insert sections is configured to provide airfoil portion optimization. 13. A hybrid turbine blade comprising: a shank portion; andan airfoil portion comprising a composite outer structure having a first mass density and a recess and at least one composite section having a first density, and at least two insert sections each having a second mass density which is less than said first mass density, the at least two insert sections disposed in alternating laminate stacked relationship with the at least one composite section and defining an alternating laminate stack of the at least one composite section and the at least two insert sections,wherein said alternating laminate stack of the at least one composite section and the at least two insert sections is disposed in said recess and having a major axis extending along a span of the airfoil portion, a minor axis extending along a chord of the airfoil portion and a thickness extending perpendicular to the major axis and through a thickness of the airfoil portion,wherein said composite outer structure and said alternating laminate stack of the at least one composite section and the at least two insert sections together define an airfoil shape, wherein said alternating laminate stack of the at least one composite section and the at least two insert sections has a stiffness and dimensional stability to maintain said airfoil shape and retain compliance and flexibility to conform to said recess,wherein said composite outer structure and said at least one composite section are comprised of a plurality of composite material layers comprising fiber filaments embedded in a matrix binder, andwherein said at least two insert sections are comprised of a material selected from the group consisting of thermoplastic materials, thermoset materials, metals, honeycomb ceramics, silicones and combinations thereof. 14. The hybrid turbine blade of claim 13, wherein said first mass density has a range from 1.4 grams per cubic centimeter to 2.0 grams per cubic centimeter. 15. The hybrid turbine blade of claim 13, wherein said second mass density has a range from 0.01 grams per cubic centimeter to 0.9 grams per cubic centimeter. 16. A method of fabricating a hybrid turbine blade comprising: laying up a plurality of composite material layers to form a portion of a composite outer structure, said portion of said composite outer structure comprising a recess; anddisposing an alternating laminate stack of at least one composite section and at least two insert sections in said recess, the laminate stack having a major axis extending along a span of the hybrid turbine blade, a minor axis extending along a chord of the hybrid turbine blade and a thickness extending perpendicular to the major axis and through a substantial thickness of the hybrid turbine blade. 17. The method of claim 16, further comprising: laying up additional composite sections and additional insert sections so as achieve a final desired thickness of the alternating laminate stack of at least one composite section and at least two insert sections and form a completed version of said alternating laminate stack of at least one composite section and at least two insert sections; andconsolidating and bonding said completed version of said alternating laminate stack of at least one composite section and at least two insert sections and said composite outer structure. 18. The method of claim 17, wherein said consolidating and bonding of said completed version of said alternating laminate stack of at least one composite section and at least two insert sections and said composite outer structure comprises using at least one of an autoclave technique, a compression mold technique, and a resin mold technique. 19. The method of claim 17, wherein said completed version of said alternating laminate stack of at least one composite section and at least two insert sections meets all mechanical load carrying requirements of said hybrid turbine blade such that no load transfer needs to occur through said at least two insert sections. 20. The method of claim 16, further comprising the step of pre-fabricating said alternating laminate stack of at least one composite section and at least two insert sections prior to disposing said alternating laminate stack in said recess.
Nelson Joey L. (Cincinnati OH) Elston ; III Sidney B. (Marbelhead MA) Tseng Wu-Yang (West Chester OH) Hemsworth Martin C. (Cincinnati OH), Counterrotating aircraft propulsor blades.
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