压气机分流环-3-筛后数据ep2995805a1_W

1、(19)TEPZZ 9958Z5A_TEP 2 995 805A1(11)EUROPEAN PATENT APPLICATION(12)(43)(51) Int Cl.:F02K 3/06 (2006.01)Date of publication:16.03.2016 Bulletin 2016/11F02C 7/05 (2006.01)(21)Application number: 15185347.0(22)Date of filing: 15.09.2015(54)NACELLE AND COMPRESSOR INLET ARRANGEMENTS(57)A gas turbine eng

2、ine (10) includes a nacelle (24)the radial distance from the first point to the second point. The relative position of the first point and the second point is governed by the ratio ofdefining a centerline axis (A) and an annular splitter (30) radially inward from the nacelle. A spinner (32) is radia

3、lly inward of the nacelle forward of a compressor section (14). A fan blade (36) extends from a fan blade platform (34). A distance X is the axial distance from a first point to a second point, wherein the first point is defined on a leading edge of the annular splitter and the second point is defin

4、ed on a leading edge of the fan blade where the fan blade meets the fan blade platform. A distance H isfor reducing foreign object debris (FOD) intake into the compressor section.Printed by Jouve, 75001 PARIS (FR)EP 2 995 805 A1(84) Designated Contracting States:AL AT BE BG CH CY CZ DE DK EE ES FI F

5、R GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TRDesignated Extension States:BA MEDesignated Validation States:MA(30) Priority: 15.09.2014 US 201462050642 P(71) Applicant: United Technologies Corporation Hartford, CT 06101 (US)(72) Inventors: SCHWARZ, Frederick M.Glastonbu

6、ry, CT Connecticut 06033 (US) MALECKI, Robert E.Storrs, CT Connecticut 06268 (US)(74) Representative: Hall, Matthew Benjamin DehnsSt Brides House10 Salisbury Square London EC4Y 8JD (GB)1EP 2 995 805 A12Descriptionfrom the first point to the second point. The relative po- sition of the first point an

7、d the second point is governedBACKGROUNDby the ratio offor reducing foreign object de-0001 The present disclosure relatesto gas turbine5bris (FOD) intake into the compressor section. The cen- terline axis and the first and second points can be defined in the same cross-sectional plane.engines, and m

8、ore particularly to nacelle and compressor inlets for geared turbofan engines, for example.0002 A gas turbine engine typically includes a com- pressor section, a combustor section, and a turbine sec- tion. In the case of a turbofan, the engine also includes a fan section. Air entering the compressor

9、 section is com- pressed and delivered into the combustor section where it is mixed with fuel and ignited to generate a high-speed exhaust gas flow. The high-speed exhaust gas flow ex- pands through the turbine to drive the compressor and the fan.0003 The fan section drives air through a bypass duct

10、. The ratio of flow through the bypass duct versus through the compressor and turbine is called the bypass ratio. To improve overall engine performance, there is a trend toward larger and larger bypass ratios. For exam- ple, in a geared turbo fan engine, a gearing system is used to connect the drivi

11、ng shaft to the fan, so the fan can rotate at a different speed from the turbine driving the fan. One aspect of this type of engine is a larger by- pass ratio than previous turbofan engines, resulting in reduced loses and less noise. One way to increase the bypass ratio is to increase the diameter o

12、f the fan section inlet, e.g. the nacelle inlet. This increase in diameter tends to increase the amount of foreign object debris (FOD) that is drawn into the fan section along with the air. While some FOD is diverted through the bypass duct, other FOD can enter into the compressor section and into t

13、he core of the engine.0004 Such conventional methods and systems have generally been considered satisfactory for their intended purpose. However, there is a continuous need in the art for improved gas turbine engines.0006 It is contemplated that the ratiocan be in10the range ofA distance r can bedef

14、ined radially from the centerline axis to the leadingedge of the annular splitter. An average distance Ravgcan be defined radially from the centerline axis to a lead- ing edge of the nacelle inlet taken over a section of the nacelle ranging from a first circumferential position to a15secondcircumfer

15、entialposition,whereinfor re-20ducing FOD intake into the compressor section. The first position can be defined on the leading edge of the nacelle inlet at a 3 oclock position and the second position can be defined on an opposing side of the leading edge of the nacelle at a 9 oclock position. The na

16、celle can include a bottom, wherein the bottom is configured to range from 14 to 66 inches off of the ground. The bypass duct and the compressor section can define a bypass ratio ranging from 10 to 16.0007 A point Z can be defined at an intersection of the centerline axis and a line C normal to the

17、centerline axis extending radially inward from the leading edge of the fan blade where the fan blade meets the fan blade platform. A point W can be defined at the intersection of the line C and the leading edge of the fan blade where the fan blade meets the fan blade platform. A distance L can be de

18、fined from the point Z to a tip of the spinner. A point V can be defined along the centerline axis at a dis- tance 0.25 x the distance L aft of the tip of the spinner. A point U can be defined at an intersection of a line E normal to the centerline axis extending radially outward from the point V an

19、d a line F extending from the point W to the tip of the spinner. A point T can be defined at an intersection of the line E and the outer surface of thespinner. A distance Mc can be defined from the point T to the point U. A distance Mp can be defined from the point T to the point V. The spinner can

20、be a substantiallyconical spinner wherein a ratio of the distance Mp to the distance Mc is less than or equal to 2. It is also contem- plated that the spinner can be a substantially ellipticalspinner wherein the ratio of the distance Mp to the dis- tance Mc can be greater or equal to 2. Lines E, F a

21、nd C,and centerline axis A can be defined in the same cross- sectional plane.0008 The gas turbine engine can also include a com- bustor section and a turbine section. The fan section, the compressor section, the combustor section and the tur-253035BRIEF DESCRIPTION400005 A gas turbine engine include

22、s a nacelle defining a centerline axis. The nacelle includes a nacelle inlet, a nacelle outlet aft of the nacelle inlet and a bypass duct therebetween. The gas turbine engine also includes a compressor section aft of the nacelle inlet, an annular splitter, a spinner, a fan blade platform, and a fan

23、blade. The annular splitter separates the bypass duct from the compressor section. The spinner is radially inward of the nacelle forward of the compressor section. The fan blade platform is defined in a fan section aft of the spinner and radially inward of the nacelle. The fan blade extends from the

24、 fan blade platform toward the nacelle. A distance X is the axial distance from a first point to a second point, wherein the first point is defined on a leading edge of the annular splitter and the second point is defined on a lead- ing edge of the fan blade where the fan blade meets the fan blade p

25、latform. A distance H is the radial distance45505523EP 2 995 805 A14bine section can be configured to produce a static thrust ranging from 24,000 to 36,000 pounds. The fan section can also include a geared fan.0009 In one embodiment, a gas turbine engine is pro- vided. The gas turbine engine having:

26、 a nacelle, the na- celle including: i. a nacelle inlet; ii. a nacelle outlet aft of the nacelle inlet; and iii. a bypass duct therebetween; a compressor section aft of the nacelle inlet; an annular splitter separating the bypass duct from the compressor section; a spinner radially inward of the nac

27、elle forward of the compressor section; a fan blade platform defined in a fan section aft of the spinner and radially inward of the nacelle; and a fan blade extending from the fan blade platform toward the nacelle, wherein a distance X is the axial distance from a first point to a second point, wher

28、ein the first point is defined on a leading edge of the annular splitter and the second point is defined on a leading edge of the fan blade where the fan blade meets the fan blade platform, and wherein a distance H is the radial distance from the first point to the second point, whereinscribed above

29、, or as an alternative to any of the foregoing embodiments, further embodiments may include a point Z that is defined at an intersection of the centerline axis and a line C normal to the centerline axis extending ra- dially inward from the leading edge of the fan blade where the fan blade meets the

30、fan blade platform, wherein a point W is defined at the intersection of the line C and the leading edge of the fan blade where the fan blade meets the fan blade platform, a distance L is defined from the point Z to a tip of the spinner, wherein a point V is defined along the centerline axis at a dis

31、tance 0.25 x the distance L aft of the tip of the spinner, wherein a point U is defined at an intersection of a line E normal to the centerline axis extending radially outward from the point V and a line F extending from the point W to the tip of the spinner, wherein a point T is defined at an inter

32、section of the line E and the outer surface of the spinner, wherein a distance Mc is defined from the point T to the point U, and wherein a distance Mp is defined from the point T to the point V, wherein the spinner is a substantially conical5101520for reducing FOD intake into thespinner whereincomp

33、ressor section.0010 In addition to one or more of the features de- scribed above, or as an alternative to any of the foregoing0016 In addition to one or more of the features de- scribed above, or as an alternative to any of the foregoing embodiments, further embodiments may include a point Z that is

34、 defined at an intersection of the centerline axis and a line C normal to the centerline axis extending ra- dially inward from the leading edge of the fan blade where the fan blade meets the fan blade platform, wherein a point W is defined at the intersection of the line C and the leading edge of th

35、e fan blade where the fan blade meets the fan blade platform, a distance L is defined from the point Z to a tip of the spinner, wherein a point V is defined along the centerline axis at a distance 0.25 times the distance L aft of the tip of the spinner, wherein a point U is defined at an intersectio

36、n of a line E normal to the centerline axis extending radially outward from the point V and a line F extending from the point W to the tip of the spinner, wherein a point T is defined at an intersection of the line E and the outer surface of the spinner, wherein a distance Mc is defined from the poi

37、nt T to the point U, and wherein a distance Mp is defined from the point T to the point V, wherein the spinner is a substantially elliptical25embodiments, whereinmay be in the rangeof300011 In addition to one or more of the features de- scribed above, or as an alternative to any of the foregoing emb

38、odiments, further embodiments may include a dis- tance r that is defined radially from the centerline axis to the first point, and an average distance Ravg is defined radially from the centerline axis to a leading edge of the nacelle inlet taken over a section of the nacelle ranging from a first pos

39、ition to a second position, wherein35400012 In addition to one or more of the features de- scribed above, or as an alternative to any of the foregoing embodiments, the first position may be defined on the leading edge of the nacelle inlet at a 3 oclock position and the second position may be defined

40、 on an opposing side of the leading edge of the nacelle at a 9 oclock position.0013 In addition to one or more of the features de- scribed above, or as an alternative to any of the foregoing embodiments, the nacelle may include a bottom, wherein the bottom is configured to range from 14 to 66 inches

41、 off of the ground.0014In addition to one or more of the features de- scribed above, or as an alternative to any of the foregoing embodiments, the bypass duct and the compressor sec- tion may define a bypass ratio ranging from 10 to 16. 0015In addition to one or more of the features de-45spinner whe

42、rein0017 In addition to one or more of the features de- scribed above, or as an alternative to any of the foregoingembodiments, further embodiments may include a com- bustor section and a turbine section wherein the fan sec- tion, the compressor section, the combustor section and the turbine section

43、 are configured to produce a specific thrust ranging from 24,000 to 36,000 pounds.0018 In addition to one or more of the features de- scribed above, or as an alternative to any of the foregoing embodiments, further embodiments may include a com- bustor section and a turbine section wherein the fan s

44、ec-505535EP 2 995 805 A16tion, the compressor section, the combustor section and the turbine section are configured to produce a specific thrust ranging from 24,000 to 36,000 pounds and wherein the fan section includes a geared fan.0019 In another embodiment a gas turbine engine is provided. The gas

45、 turbine engine having: a nacelle de- fining a centerline axis, the nacelle including: i. a nacelle inlet; ii. a nacelle outlet aft of the nacelle inlet; and iii. a bypass duct therebetween; a compressor section aft of the nacelle inlet; a combustor section aft of the compres- sor section; a turbine

46、 section aft of the combustor section, wherein the fan section, the compressor section, the combustor section and the turbine section are configured to produce a specific thrust ranging from 24,000 to 36,000 pounds; an annular splitter separating the bypass duct from the compressor section; a spinne

47、r radially inward of the nacelle forward of the compressor section; a fan blade platform defined in a fan section aft of the spinner and radially inward of the nacelle; and a fan blade ex- tending from the fan blade platform toward the nacelle, wherein a distance X is the axial distance from a first

48、 point to a second point, wherein the first point is defined on a leading edge of the annular splitter and the second point is defined on a leading edge of the fan blade where the fan blade meets the fan blade platform, and wherein a distance H is the radial distance from the first point to0023 In a

49、ddition to one or more of the features de- scribed above, or as an alternative to any of the foregoing embodiments, the bypass duct and the compressor sec- tion may define a bypass ratio ranging from 10 to 16. 0024 In addition to one or more of the features de- scribed above, or as an alternative to

50、 any of the foregoing embodiments, further embodiments may include a point Z that is defined at an intersection of the centerline axis and a line C normal to the centerline axis extending ra- dially inward from the leading edge of the fan blade where the fan blade meets the fan blade platform, where

51、in a point W is defined at the intersection of the line C and the leading edge of the fan blade where the fan blade meets the fan blade platform, a distance L the is defined from the point Z to a tip of the spinner, wherein a point V is defined along the centerline axis at a distance 0.25 x the dist

52、ance L aft of the tip of the spinner, wherein a point U is defined at an intersection of a line E normal to the centerline axis extending radially outward from the point V and a line F extending from the point W to the tip of the spinner, wherein a point T is defined at an intersection of the line E

53、 and the outer surface of the spinner, wherein a distance Mc is defined from the point T to the point U, and wherein a distance Mp is defined from the point T tothe point V, wherein the spinner is a substantially conical510152025spinner, and whereinthe second point, whereinfor reduc-0025 In addition

54、 to one or more of the features de- scribed above, or as an alternative to any of the foregoing embodiments, further embodiments may include a point Z that is defined at an intersection of the centerline axis and a line C normal to the centerline axis extending ra- dially inward from the leading edg

55、e of the fan blade where the fan blade meets the fan blade platform, wherein a point W is defined at the intersection of the line C and the leading edge of the fan blade where the fan blade meets the fan blade platform, a distance L is defined from the point Z to a tip of the spinner, wherein a poin

56、t V is defined along the centerline axis at a distance 0.25 times the distance L aft of the tip of the spinner, wherein a point U is defined at an intersection of a line E normal to the centerline axis extending radially outward from the point V and a line F extending from the point W to the tip of

57、the spinner, wherein a point T is defined at an intersection of the line E and the outer surface of the spinner, wherein a distance Mc is defined from the point T to the point U, and wherein a distance Mp is defined from the point T to the point V, wherein the spinner is a substantially ellipticalin

58、g FOD intake into the compressor section, and wherein a distance r is defined radially from the centerline axis to the first point, and an average distance Ravg is defined radially from the centerline axis to a leading edge of the nacelle inlet taken over a section of the nacelle ranging from a first position to a second position, wherein3035alsofor reducing FOD debris intake into the compressor sec- tion.0020In addition to one or more of the features de- scribed above, or as an alternative to any of the