[특허]Forward compartment baffle arrangement for a geared turbofan engine

Forward compartment baffle arrangement for a geared turbofan engine 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F01D-025/18 F01D-025/24 F02K-003/06 F02C-007/06 F02C-007/36
출원번호	US-0709153 (2012-12-10)
등록번호	US-9896968 (2018-02-20)
발명자 / 주소	DiBenedetto, Enzo NguyenLoc, Fred
출원인 / 주소	United Technologies Corporation
대리인 / 주소	Bachman & LaPointe, P.C.
인용정보	피인용 횟수 : 0 인용 특허 : 40

초록

A baffle within a gas turbine engine includes a cylindrical flange with a multiple of holes at least partially therearound.

대표청구항 ▼

1. An engine case assembly within a gas turbine engine comprising: a baffle located radially inboard of an annular core flow path of the gas turbine engine, said baffle defined around an engine central longitudinal axis, wherein said baffle defines an axial length approximately 70%+25%/−30% of an axial length of said front center body from a forward most inner diameter bolt flange to an aft most inner diameter bolt flange, said baffle having a cylindrical flange with a multiple of holes at least partially therearound. 2. The assembly as recited in claim 1, wherein said baffle projects into the front center body, starting from a similar axial position at the forward most inner diameter bolt flange. 3. The assembly as recited in claim 1, further comprising an oil recovery gutter axially offset from said multiple of holes. 4. The assembly as recited in claim 3, wherein said oil recovery gutter is radially offset from said flange. 5. The assembly as recited in claim 1, wherein said multiple of holes are defined in a multiple of rows. 6. The assembly as recited in claim 1, wherein said cylindrical flange extends from a bearing support. 7. The assembly as recited in claim 1, wherein said cylindrical flange extends from the front center body. 8. A gas turbine engine comprising: an epicyclic gear system with a multiple of oil passages that extend through a ring gear of said epicyclic gear system; a bearing support;a baffle mounted to said bearing support to at least partially surround said epicyclic gear system, said baffle having an oil recovery gutter outboard of said multiple of oil passages, and a multiple of holes downstream of said oil recovery gutter, said oil recovery gutter axially aligned with said multiple of oil passages to receive oil slung therefrom. 9. The gas turbine engine as recited in claim 8, wherein said epicyclic gear system is a planetary gear system. 10. The gas turbine engine as recited in claim 8, wherein said epicyclic gear system is a star gear system. 11. The gas turbine engine as recited in claim 8, wherein said bearing support is a #1/1.5 bearing support that defines a cylindrical flange that extends axially therefrom relative to an engine central longitudinal axis. 12. The gas turbine engine as recited in claim 11, wherein said cylindrical flange extends from a front center body that defines the annular core flow path. 13. The gas turbine engine as recited in claim 8, further comprising a knife seal engaged with said baffle. 14. The gas turbine engine as recited in claim 8, wherein said oil recovery gutter is manufactured of a softer material than said knife seal. 15. The gas turbine engine as recited in claim 8, further comprising a bypass channel defined by said baffle. 16. The gas turbine engine as recited in claim 8, wherein said baffle defines an axial length approximately 70%+25%/−30% of an axial length of a front center body. 17. The assembly as recited in claim 8, wherein said oil is radially expelled through a ring gear of the epicyclic gear system through the multiple of oil passages toward the baffle. 18. An engine case assembly a gas turbine engine comprising: a front center body that at least partially defines an annular core flow path; anda baffle that extends from said front center body forward with respect to the core airflow through the annular core flow path into a low pressure compressor, said baffle extends toward a separate oil recover gutter. 19. The assembly as recited in claim 18, wherein said baffle is integral with said front center body. 20. The assembly as recited in claim 18, wherein said baffle extends toward a an oil recover gutter. 21. The assembly as recited in claim 20, wherein said baffle includes a cylindrical flange with multiple of holes at least partially therearound. 22. The assembly as recited in claim 21, wherein said baffle is separate from said oil recover gutter. 23. The assembly as recited in claim 18, further comprising an oil recovery gutter axially offset from said multiple of holes. 24. The assembly as recited in claim 18, further comprising an epicyclic gear system with a multiple of oil passages that extend through a ring gear of said epicyclic gear system, said multiple of holes are axially offset from said multiple of oil passages.

이 특허에 인용된 특허 (40)

Vdoviak John W. (Marblehead MA), Aircraft engine frame construction.
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Wilson, Bary W.; Peters, Timothy J.; Shepard, Chester L.; Reeves, James H., Apparatus and method for fluid analysis.
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Peters,Robert E.; Messerschmidt,Dwayne; Glahn,J. Axel; Allard,Kenneth L.; Jen,Hsianmin F.; Spires,Larry W.; Barnsby,Roger M., Bifurcated oil scavenge system for a gas turbine engine.
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Lindberg John E. (Lafayette CA), Combustion and pollution control system.
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Lindberg John E. (Lafayette CA), Combustion and pollution control system.
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Andersen Richard H. (Cincinnati OH) Corsmeier Robert J. (Cincinnati OH) Rauf James P. (Blue Ash OH) Lenahan Dean T. (Cincinnati OH), Cooling air cooler for a gas turbine engine.
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Krul Allan D. ; Harris ; Jr. J. Wesley, Deoiler shaft vortex separator.
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Sheridan, William G.; McCune, Michael E., Epicyclic gear system with improved lubrication system.
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McCune, Michael E., Epicyclic gear system with superfinished journal bearing.
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Sheridan, William G.; McCune, Michael E.; Pescosolido, Alessio, Flexible shaft for gas turbine engine.
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Smith Stanley (Gloucestershire GB2), Fluid processing device.
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Legare, Pierre-Yves; Herborth, Jason Todd; Arthur, Glen Owen, Impeller baffle with air cavity deswirlers.
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Dittmar,Kevin S.; Edmonds,David H.; Schenk,Bjoern; Sheoran,Yogendra Y., Integrated gearless and nonlubricated auxiliary power unit.
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Midgley Ronald A. (St. Albans GB2), Lubrication system.
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Henry, Mark Stephen; Wellborn, Steven Robert, Lubrication system for a bearing.
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McKibbin Albert H. (Cromwell CT), Lubrication system for a planetary gear train.
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Moseley Thomas S. (2501 Briggs Chaney Rd. Silver Spring MD 20905), Method and apparatus for efficiently compressing a gas.
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Sheridan, William G.; McCune, Michael E., Method for assembling an epicyclic gear train.
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Nguyen, Ly D.; Cruse, Louis; Fowkes, Ivar Gene; Salas, Silvestre; North, William; Kadambi, Vadanth, Method of forming a thermally isolated gas turbine engine housing.
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Sheridan, William G.; McCune, Michael E., Oil baffle for gas turbine fan drive gear system.
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Sheridan, William G.; McCune, Michael E., Oil baffle for gas turbine fan drive gear system.
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Thebert Glenn W. (Carmel IN), Oil scavenge system.
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Alecu, Daniel T.; Parkman, Kenneth, Oil scavenge system having churning damper for gas turbine engines.
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Clark Ralph J. (Rochester MI), Oil scavening system for gas turbine engine.
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Proeschel, Richard Alan, Reciprocating hot air bottom cycle engine.
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Jewess Gordon (San Diego CA), Seal construction for use in a turbine engine.
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Malott Richard C. (Indianapolis IN), Shield for labyrinth seal.
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Moseley Thomas S. (2501 Briggs Chaney Rd. Silver Spring MD 20905), Thermal sweep insulation system for minimizing entropy increase of an associated adiabatic enthalpizer.
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Nguyen, Ly D.; Cruse, Louis; Fowkes, Ivar Gene; Salas, Silvestre; North, William; Kadambi, Vadanth, Thermally isolated housing in gas turbine engine.
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Johnson, James E., Turbine engine with modulated flow fan and method of operation.
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Lasker, George, Uncoupled, thermal-compressor, gas-turbine engine.
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Forward compartment baffle arrangement for a geared turbofan engine 원문보기

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Forward compartment baffle arrangement for a geared turbofan engine 원문보기

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