第四组5-专利全文外文wo2015065587

1、(12) INTERNATIONAL APPLICATION PUBLISHED UNDER THE PATENT COOPERATION TREATY (PCT)(19) World Intellectual Property OrganizationInternational Bureau(43) International Publication Date 7 May 2015 (07.05.2015)(10) International Publication NumberWO 2015/065587 AlP OP C T(51)International Patent Classif

2、ication:(81)Designated States (unless otherwise indicated, for every kind of national protection available): AE, AG, AL, AM, AO, AT, AU, AZ, BA, BB, BG, BH, BN, BR, BW, BY,BZ, CA, CH, CL, CN, CO, CR, CU, CZ, DE, DK, DM,DO, DZ, EC, EE, EG, ES, FI, GB, GD, GE, GH, GM, GT,HN, HR, HU, ID, IL, IN, IR, IS

3、, JP, KE, KG, KN, KP, KR,KZ, LA, LC, LK, LR, LS, LU, LY, MA, MD, ME, MG,MK, MN, MW, MX, MY, MZ, NA, NG, NI, NO, NZ, OM,PA, PE, PG, PH, PL, PT, QA, RO, RS, RU, RW, SA, SC,SD, SE, SG, SK, SL, SM, ST, SV, SY, TH, TJ, TM, TN,TR, TT, TZ, UA, UG, US, UZ, VC, VN, ZA, ZM, ZW.Designated States (unless otherw

4、ise indicated, for every kind of regional protection available): ARIPO (BW, GH, GM, KE, LR, LS, MW, MZ, NA, RW, SD, SL, ST, SZ, TZ, UG, ZM, ZW), Eurasian (AM, AZ, BY, KG, KZ, RU, TJ, TM), European (AL, AT, BE, BG, CH, CY, CZ, DE, DK, EE, ES, FI, FR, GB, GR, HR, HU, IE, IS, IT, LT, LU,LV, MC, MK, MT,

5、 NL, NO, PL, PT, RO, RS, SE, SI, SK,SM, TR), OAPI (BF, BJ, CF, CG, CI, CM, GA, GN, GQ, GW, KM, ML, MR, NE, SN, TD, TG).F02C 7/24 (2006.01)F02C 7/12 (2006.01)F01D 25/12 (2006.01)(21)International Application Number:PCT/US20 14/054081(22)International Filing Date:4 September 2014 (04.09.2014)English E

6、nglish(25)(26)(30)Filing Language:Publication Language: Priority Data:(84)61/899,5524 November 2013 (04. 11.2013)US(71)Applicant: UNITED TECHNOLOGIES CORPORATION US/US; 1 Financial Plaza, Hartford, Connecticut 06101 (US).Inventors: BURD, Steven W.; 36 Renee Court, Cheshire, Connecticut 06410 (US). B

7、RDAR, Christopher R.; 500 Cold Spring Road, Apt. E306, Rocky Hill, Connecticut 06067 (US). PHILIPPONA, Derk S.; 163 Charles Street, Tolland, Connecticut 06084 (US).Agent: OSHEA, Patrick J.; OShea Getz P.C. , 1500 Main Street, Suite 912, Springfield, MA 0 1115-5227 (US).(72)Published:with internation

8、al search report (Art. 21(3)(74)(54) Title: COATED COOLING PASSAGE00 oo(57) Abstract: A component for a gas turbine engine includes a substrate with a substrate aperture and a coating on the substrate that extends a length of the substrate aperture. A liner assembly for a gas turbine engine includes

9、 a hot sheet with a multiple of apertures and a coating on the hot sheet that extends a length of each of the multiple of apertures. A method of forming an aperture to provide film cooling in a component of a gas turbine engine, includes forming a multiple of substrate apertures in a substrate. Each

10、 of the multiple of substrate apertures defines a substrate inner periphery. A coating is applied on the substrate after forming the multiple of substrate apertures to define a coating inner periphery at least partially within each of the multiple of substrate apertures. The coating inner periphery

11、is smaller than the substrate inner periphery.COATED COOLING PASSAGECROSS-REFERENCE TO RELATED APPLICATIONThis application claims priority to U.S. Provisional Application No. 61/899,552 filedNovember 4, 2013, which is hereby incorporated herein by reference in its entirety.STATEMENT REGARDING FEDERA

12、LLY SPONSORED RESEARCH OR DEVELOPMENT0001This disclosure was made with Government support under N00019-02-C-3003 awarded by the United States Air Force. The Government may have certain rights in thisdisclosure.BACKGROUND0002The present disclosure relates to gas turbine engines, and more particularly

13、 toan exhaust duct therefor.0003Gas turbine engines, such as those which power modern military andcommercial aircraft, include a compressor section to pressurize a supply of air, a combustorsection to burn a hydrocarbon fuel in the presence of the pressurized air, and a turbine section toextract ene

14、rgy from the resultant combustion gases and generate thrust.Downstream of theturbine section, military aircraft engines often include an augmentor section, or afterburner,operable to selectively increase thrust. The increase in thrust is produced when fuel is injectedinto the core exhaust gases down

15、stream of the turbine section and burned with the oxygencontained therein to generate a second combustion.0004The augmentor section and downstream exhaust duct and nozzle sections maybe exposed to high temperature exhaust gases such that a liner assembly is disposed between theexhaust gas and the ex

16、haust duct to provide thermal protection and/or acoustic damping. Thesemay be of single or double walled construction, with a hot sheet and a cold sheet. The hot sheetmay have a thermal barrier or radar signature reduction coating. The exhaust gas temperaturesmay in some instances exceed the metalli

17、c alloy capabilities in these sections such that filmcooling is provided therefor.The cooling air is provided though numerous cooling holes tosheath the hardware from the exhaust gases. The cooling holes are typically produced via a laserdrill through the coated substrate.SUMMARY0005A component for

18、a gas turbine engine, according to one disclosed non-limitingembodiment of the present disclosure, includes a substrate with a substrate aperture and a coatingon the substrate that extends a length of the substrate aperture.0006In a further embodiment of the present disclosure, the coating is thicke

19、r than athickness of the substrate.0007In a further embodiment of any of the foregoing embodiments of the presentdisclosure, a thickness of the coating is between 10%- 100% of a characteristic diameter of thesubstrate aperture.0008In a further embodiment of any of the foregoing embodiments of the pr

20、esentdisclosure, the coating is a thermal barrier coating.In a further embodiment of any of the foregoing embodiments of the present0009disclosure, the coating is a signature reduction coating.0010In a further embodiment of any of the foregoing embodiments of the presentdisclosure, the coating is ab

21、out between 0.010 - 0.1 inches (0.254 - 2.54mm) thick.0011In a further embodiment of any of the foregoing embodiments of the presentdisclosure, the substrate aperture defines a raised area toward a backside of the substrate.0012In a further embodiment of any of the foregoing embodiments of the prese

22、ntdisclosure, the coating defines a coating inner periphery at least partially within a substrate innerperiphery. The coating inner periphery is smaller than the substrate inner periphery.0013In a further embodiment of any of the foregoing embodiments of the presentdisclosure, the coating inner peri

23、phery defines an angle with respect to an axis of the substrateaperture.0014A liner assembly for a gas turbine engine, according to another disclosed non-limiting embodiment of the present disclosure, includes a hot sheet with a multiple of aperturesand a coating on the hot sheet that extends a leng

24、th of each of the multiple of apertures.0015In a further embodiment of any of the foregoing embodiments of the presentdisclosure, a cold sheet is included and spaced from the hot sheet. The cold sheet and the hotsheet are within an exhaust duct of a gas turbine engine.0016In a further embodiment of

25、any of the foregoing embodiments of the presentdisclosure, the coating defines a coating inner periphery at least partially within a substrate innerperiphery of each of the multiple of apertures. The coating inner periphery is smaller than thesubstrate inner periphery.0017In a further embodiment of

26、any of the foregoing embodiments of the presentdisclosure, the coating inner periphery defines an angle with respect to an axis of the substrateaperture.0018In a further embodiment of any of the foregoing embodiments of the presentdisclosure, the coating defines an unequal thickness within the subst

27、rate inner periphery.A method of forming an aperture to provide film cooling in a component of a0019gas turbine engine, according to another disclosed non-limiting embodiment of the presentdisclosure, includes forming a multiple of substrate apertures in a substrate and applying acoating on the subs

28、trate after forming the multiple of substrate apertures to define a coating innerperiphery at least partially within each of the multiple of substrate apertures.0020In a further embodiment of any of the foregoing embodiments of the presentdisclosure, the method includes applying the coating at a non

29、-perpendicular angle to thesubstrate.0021In a further embodiment of any of the foregoing embodiments of the presentdisclosure, the method includes punching the multiple of substrate apertures in the substrate froma front side to form a raised region on a backside of the substrate.0022In a further em

30、bodiment of any of the foregoing embodiments of the presentdisclosure, the method includes laser drilling the multiple of substrate apertures in the substrate.0023In a further embodiment of any of the foregoing embodiments of the presentdisclosure, the coating inner periphery defines an angle with r

31、espect to an axis of the substrateaperture.0024In a further embodiment of any of the foregoing embodiments of the presentdisclosure, the coating defines an unequal thickness around the substrate inner periphery.0025The foregoing featuresandelements may becombined invariouscombinations without exclus

32、ivity, unless expressly indicated otherwise.These features andelements as well as the operation thereof will become more apparent in light of the followingdescription and the accompanying drawings.It should be understood, however, the followingdescription and drawings are intended to be exemplary in

33、 nature and non-limiting.BRIEF DESCRIPTION OF THE DRAWINGS0026Various features will become apparent to those skilled in the art from thefollowing detailed description of the disclosed non-limiting embodiments.The drawings thataccompany the detailed description can be briefly described as follows:002

34、7FIG. 1 is a general schematic view of an exemplary gas turbine engine for usewith the present disclosure;0028FIG. 2 is a perspective cross section of an exhaust duct section according toone non-limiting embodiment;0029FIG. 3 is a cross section through a passage according to one non-limitingembodime

35、nt;0030FIG. 4 is a cross section through a passage according to another non-limitingembodiment; andFIG. 5 is a flow chart of a coating application process.0031DETAILED DESCRIPTIONFIG. 1 schematically illustrates a gas turbine engine 20.The gas turbine0032engine 20 is disclosed herein as a two-spool

36、low-bypass augmented turbofan that generallyincorporates a fan section 22, a compressor section 24, a combustor section 26, a turbine section28, an augmenter section 30, an exhaust duct section 32, and a nozzle section 34 along a centrallongitudinal engine axis A. Although depicted as an augmented l

37、ow bypass turbofan in thedisclosed non-limiting embodiment, it should be understood that the concepts described hereinare applicable to other gas turbine engines, including, for example, non-augmented engines,geared architecture engines, direct drive turbofans, turbojet, turboshaft, multi-stream var

38、iablecycle, ramjet and other engine architectures as well as within other engine sections such as thecombustor section 26.0033An outer structure 36 and an inner structure38 define a generally annularsecondary airflow path 40 around a core primary airflow path 42.Various structure and modulesmay defi

39、ne the outer structure 36 and the inner structure 38 which essentially define anexoskeleton to support the rotational hardware therein.0034Air that enters the fan section 22 is divided between a primary airflow throughthe primary airflow path 42 and a secondary airflow through the secondary airflow

40、path 40. Theprimary airflow passes through the combustor section 26, the turbine section 28, then theaugmentor section 30 where fuel may be selectively injected and burned to generate additionalthrust through the nozzle section 34.It should be appreciated that additional airflow streamssuch as third

41、 stream airflow typical of variable cycle engine architectures may additionally besourced from the fan section 22.0035The secondary airflow may be utilized for a multiple of purposes to include,for example, cooling and pressurization. The secondary airflow as defined herein is any airflowdifferent f

42、rom the primary airflow. The secondary airflow may ultimately be at least partiallyinjected into the primary airflow path 42 adjacent to the exhaust duct section 32 and the nozzlesection 34.0036With reference to FIG. 2, the exhaust duct section 32 generally includes anouter exhaust duct case 44 (ill

43、ustrated schematically) of the outer structure 36 and a linerassembly 46 spaced inward therefrom. The exhaust duct section 32 may be circular in cross-section as typical of an axis-symmetric augmented low bypass turbofan, non-axisymmetric incross-section, as well as other shapes to include, but not

44、be limited to, an oval cross-section, arectilinear cross-section or combinations thereof. In addition to the various cross-sections, theexhaust duct section 32 may be non-linear with respect to the central longitudinal engine axis Ato form, for example, a serpentine shape to block direct view to the

45、 turbine section 28.Furthermore, in addition to the various cross-sections and the various longitudinal shapes, theexhaust duct section 32 may terminate in the nozzle section 34 (see FIG. 1) which may be aconvergent divergent nozzle, a non-axisymmetric two-dimensional (2D) vectorable nozzlesection,

46、a flattened slot convergent nozzle of high aspect ratio or other exhaust duct arrangement.0037The liner assembly 46 operates as a heat shield to protect the outer exhaustduct case 44 from the high temperature exhaust gases in the primary airflow path 42 downstreamof the turbine section 28.Secondary

47、air discharged from, for example, the fan section 22 orcompressor section 24, is communicated through an annular passageway 48 defined between theouter exhaust duct case 44 and the inner liner assembly 46. Since the secondary air is relativelycool compared to the exhaust gases in the primary airflow

48、 path 42, the secondary air cools theliner assembly 46 to enhance the life and reliability thereof.0038The liner assembly 46 may include a cold sheet 50 separated from a hot sheet52 by a plurality of structural supports 54 which attach the cold sheet 50 to the hot sheet 52.During engine operation, t

49、he cold sheet 50 receives relatively large pressure loads anddeflections, while the hot sheet 52 receives relatively small pressure loads and deflections andthereby better retains ceramic coatings. It should be appreciated that various types of structuralsupports as well as locations therefore may b

50、e used herewith and that the illustrated structuralsupports 54 is but one non-limiting examples.0039The cold sheet 50 may be corrugated with various rippled or non-planarsurfaces and include a multiple of metering passages 56 to receive secondary airflow frombetween the outer exhaust duct case 44 an

51、d the liner assembly 46. The secondary airflow iscommunicated through passages 58 in the hot sheet 52. The passages 58 provide film coolingand are generally more prevalent than the metering passages 56 which provide impingementcooling to the hotsheet 52.The secondary airflow thereby provides impinge

52、ment and filmcooling to sheaththe liner assembly 46 from the relatively high temperature combustionproducts. In another disclosed non-limiting embodiment, the passages 58 may provide acousticdampening.0040The hot sheet 52 includes a backside 62 that faces the cold sheet 50 and afront side 64 opposit

53、e the backside 62 on the exhaust gas path side of the hot sheet 52. The frontside 64 is that which is directly in contact with the relatively high temperature exhaust gases,which in this disclosed non-limiting embodiment, may be generated by secondary combustion inthe augmenter section 30 (see FIG.

54、1).0041As further discussed below with respect to FIGS. 3-4, the front side 64includes a coating 60 such as a thermal barrier or radar signature reduction coating. Althoughthe hot sheet 52 is illustrated herein as representative of a substrate 66 with the coating 60, itshould be appreciated that var

55、ious coated components that, for example, provide environmentalprotection, heat resistance, signature reduction and/or acoustic damping will also benefitherefrom. In one example, the substrate 66 is about equal in thickness to the coating 60 and maybe between about 0.010 - 0.1 inches (0.254 - 2.54mm

56、). More specifically, the coating 60 maybe between 20%-200% the thickness of the substrate 66 applied to the front side 64.0042With reference to FIG. 3, each passage 58 in this disclosed non-limitingembodiment includes a substrate aperture 70 formed in the substrate 66 through, for example,cutting,

57、punching, drilling, laser drilling or other formation technique. In one disclosednon-limiting embodiment, the substrate includes a raised region 7 1 on the backside 62 thereof as thepassage 58 is formed from the front side 64. The raised region 7 1 is a generally protruding areaon the backside 62 and may at least partially surround the periphery of the passage 58 as typicalof