3-筛选及标引后的专利著录项目数据及专利全文us8052085b2

1、I 1111111111111111 111111111111111 111111111111111 1111111111 lll111111111111111US008052085B2c12) United States Patent(IO) Patent No.:US 8,052,085 B2Lair(45) Date of Patent:Nov. 8, 2011(54) THRUST REVERSER FORA TURBOFAN GAS TURBINE ENGINE(75) Inventor: Jean-Pierre Lair, San Antonio, TX (US)4,129,269

2、 A4,147,027 A *4,175,385 A4,182,501 A4,212,442 A4,232,516 A12/1978 Fage4/1979 Greathouse.60/226.211/1979 Nash 1/1980 Fage 7/1980 age 11/1980 Lewis et al(73) Assignee: The NORDAM Gronp, Inc., Tulsa, OK4,292,803 A10/1981 Prior(US)4,362,015 A12/1982 Fage(*)Notice:Subject to any disclaimer, the term oft

3、his4,4224,6659 A12/1983 Fage 1/1984 Fagepatent is extended or adjusted under 354,519,561 A5/1985 Timms4,581,890 A4/1986 GiraudU.S.C. 154(b) by 893 days.4,682,733 A7/1987 Newton 4,801,112 A1/1989 Fournier(21) Appl. No.: 11/941,378(22) Filed:Nov. 16, 2007(65)Prior P11blication Data US 2009/0127390AlMa

4、y 21, 2009(51) Int. Cl.F02K 1154(2006.01)(52) U.S. Cl. . 244/110 B; 60/226.2; 239/265.29(58) Field of Classification Search244/12.5244/23 D, 110 B; 60/226.2, 230; 239/265.25,239/265.29See application file for complete search history(56)References CitedU.S. PATENT DOCUMENTS2,847,823A8/1958Brewer3,002

5、,342A*10/1961Schatzki239/127.33,347,578A10/1967Sheehan et al3,492,821A2/1970Monaghan et al3,541,794A1111970Johnston et al3,550,855A12/1970Feld et al3,610,534A10/1971Medawar3,640,468A2/1972Searle et al3,660,982A5/1972Gozlan3,684,182A8/1972Maison3,856,239A12/1974Leibach4,047,381A9/1977Smith4,830,519 A

6、5/1989 Starke(Continued)FOREIGN PATENT DOCUMENTSFR26010771/1988(Continued)OTHER PUBLICATIONSU.S. Appl. No. 11/941,360, filed Nov. 16, 2007, entitled Thrust Reverser Door, by Jean-Pierre Lair(Continued)Primary Examiner - Tien DinhAssistant Examiner - Joseph W Sanderson(74) Attorney, Agent, or Firm -

7、Francis L. Conte(57)ABSTRACTThe thrust reverser includes, in one aspect, an interior flow deflector which defines a portion of a substantially continu ous and uninterrupted nozzle interior surface with the interior of a jet pipe when the door is in a stowed position, thereby reducing aerodyn 皿 ic lo

8、sses and improving efficiency. ln another aspect, improved sealing a盯 angement between the jet pipe and the door provides increased performance when the doors are stowed.26 Claims, 8 Drawing Sheets伽.巨 32泛 a匆/US 8,052,085 B2Page 35,852,928A12/1998Vauchel5,853,148Al 2/1998Standish5,863,014Al/ 1999Stan

9、dish5,875,995A3/1999Moe5,893,265A4/1999Gonidec5,899,059A5/1999Gonidec5,904,041A5/1999Dhainault5,913,476A6/1999Gonidec5,927,647A7/1999Masters5,930,991A8/1999Fournier5,934,613A8/1999Standish5,937,636A8/1999Gonidec5,947,625A9/1999Vauchel5,956,939A9/1999Fage5,960,626A10/1999Baudu5,967,460A10/1999Baudu5,

10、970,704A10/1999Lardy5,974,783A1111999Gonidec5,983,625A1111999Gonidec5,987,881A1111999Gonidec5,996,937A12/1999Gonidec5,997,054A12/1999Baudu6,000,216A12/1999Vauchel6,009,702A1/2000Gonidec6,026,638A2/2000Gonidec6,027,071A2/2000Lair6,029,439A2/2000Gonidec6,032,901A3/2000Carimali6,044,641A4/2000Baudu6,04

11、5,091A4/2000Baudu6,065,285A5/2000Gonidec6,068,213A5/2000Gonidec6,076,347A6/2000Gonidec6,079,201A6/2000Jean6,082,096A7/2000Vauchel6,094,908A8/2000Baudu6,101,807A8/2000Gonidec6,105,439A8/2000Roger6,145,301A11/2000Gonidec6,145,786A11/2000Baudu6,148,607A11/2000Baudu6,151,884A11/2000Gonidec6,151,885A11/2

12、000Metezeau6,151,886A11/2000Vauchel6,158,211A12/2000Gonidec6,170,254Bl1/2001Cariola6,170,255Bl1/2001Gonidec6,173,807Bl1/2001Welch et al6,216,980Bl4/2001Baudu6,237,325Bl5/2001Hogie6,256,979Bl7/2001Fourmer6,260,801Bl7/2001Peters6,276,026Bl8/2001Wille6,293,495Bl9/2001Aten6,357,672Bl3/2002Cowan et al6,3

13、85,964B25/2002Jean6,402,092Bl6/2002Jean6,438,942B28/2002Fourmer6,487,845Bl12/2002Modglin6,546,715Bl4/2003Blevins6,546,716B24/2003Lair6,568,172B25/2003Jannetta et al6,584,763B27/2003Lymons6,592,074B27/2003Dehu6,622,964B29/2003Rouyer6,688,098B22/2004Rouyer6,688,099B22/2004Lair6,751,944B26/2004Lair6,78

14、6,038B29/2004Lair6,804,947B210/2004Le Docte6,820,410B211/2004Lair6,845,607B21/2005Lair6,845,946B21/2005Lair6,895,742B25/2005Lair et al6,910,328Bl6/2005Joyce6,926,234B28/2005Colotte6,938,408B29/2005Lair6,945,031B29/2005Lair6,966,175B211/2005LairU.S. PATENT DOCUMENTS4,836,451A6/1989Herrick et al4,860,

15、956A8/1989Fage4,865,256A9/1989Durand4,894,985Al/ 1990Dubois4,909,346A3/1990Torkelson4,914,905A4/1990Dubois4,916,895A4/1990Dubois4,922,712A5/1990Matta4,922,713A5/1990Barbarin4,960,243A10/1990Dubois4,966,327A10/1990Fage et al4,976,466A12/1990Vauchel4,998,409A3/1991Mutch5,003,770A4/1991Schegerin5,039,1

16、71A8/1991Lore5,040,730A8/1991Hogie5,083,426Al/ 1992Layland5,090,197A2/1992Dubois5,097,661A3/1992Lair et al5,101,621A4/1992Mutch5,117,630A6/1992Cariola5,120,004A6/1992Matthias5,167,118A12/1992Torkelson5,176,340A1/1993Lair5,181,676A1/1993Lair5,192,023A3/1993Fage et al5,197,693A3/1993Remlaoui5,203,525A

17、4/1993Remlaoui5,209,057A5/1993Remlaoui5,211,008A5/1993Fage5,221,048A6/1993Lair5,224,342A7/1993Lair5,228,641A7/1993Remlaom5,230,213A7/1993Lawson5,243,817A9/1993Matthias5,251,435A10/1993Pauley5,267,438A12/1993Bunel5,284,015A2/1994Carimah5,297,387A3/1994Carimali5,309,711A5/1994Matthias5,310,117A5/1994F

18、age et al5,347,808A9/1994Standish5,372,006A12/1994Lair5,390,879A2/1995Lair5,392,991A2/1995Gatti5,396,762A3/1995Standish5,419,515A5/1995Lair5,440,875A8/1995Torkelson5,473,886A12/1995Lebrun5,524,431A6/1996Brusson5,548,954A8/1996de Cambray5,558,594A9/1996Lefranc5,615,549A4/1997Valleroy5,615,834A4/1997O

19、sman5,655,360A8/1997Butler5,666,802A9/1997Lair5,671,598A9/1997Standish5,716,025A2/1998Meyer5,720,449A2/1998Laboure5,725,182A3/1998Valleroy5,727,380A3/1998Lardy et al5,730,392A3/1998Lair5,765,362A6/1998Gonidec5,775,097A7/1998Lardy5,775,639A7/1998Fage5,778,659A7/1998Duesler5,778,660A7/1998Jean5,779,19

20、2A7/1998Metezeau et al5,782,434A7/1998Jean5,785,249A7/1998Metezeau5,794,433A8/1998Peters5,799,903A9/1998Vauchel5,806,302A9/1998Cariola5,813,220A9/1998Portal5,819,527A10/1998Fournier5,819,528A10/1998Masson5,826,823A10/1998Lymons5,836,149A1111998Servanty6,968,675B211/2005R扣nlaoui et al6,971,2296,976,3

21、52B2 B212/200512/2005Lair LairWO6,983,588B21/2006LairWO6,993,819B22/2006Homann7,007,454B23/2006DehuFOREIGN PATENT DOCUMENTS 86/00862 Al2/1986WO 9855754 Al * 12/1998OTHER PUB口CATIONS7,010,905B23/2006Lair7,043,897B25/2006Osman7,055,329B26/2006Martens et alU.S. Appl. No. 11/941,371, filed Nov. 16, 2007

22、, entitled Pivotmg Door Thrust Reverser for a Turbofan Gas Turbine Engine, by Jean7,093,793B28/2006LairPierre Lair7,127,880B210/2006LairU.S. Appl. No. 11/941,395, filed Nov. 16, 2007, entitled Pivotmg7,146,796B212/2006LairFairings for a Thrust Reverser, by Jean-Pierre Lair7,229,247B26/2007Durocher e

23、t alU.S. Appl. No. 11/941,391, filed Nov. 16, 2007, entitled Thrust7,255,307B28/2007MayesReverser Door, by Jean-Pierre LairRE39,972E1/2008RoyaltyU.S. Appl. No. 11/941,388, filed Nov. 16, 2007, entitled Thrust2004/0139726Al7/2004ColotteReverser, by Jean-Pierre Lair2005/0151012Al7/2005LairU.S. Appl. N

24、o. 12/142,084, filed Jun. 19, 2008, entitled Thrust2005/0183894Al8/2005LairReverser for a Turbofan Gas Turbine Engine, by Jean-Pierre Lair2006/0005530Al1/2006Blinand Paul Weaver2006/0288688Al12/2006Lair2008/0072570Al3/2008Lair* cited by examinerU.S. PatentNov. 8, 2011Sheet 1 of 8us 8,052,085 B2A 、 沁

25、叶 l _ _ a U.S. PatentUS 8,052,085 B2Nov. 8, 2011Sheet 2 of 8 q 、 们 、 $ 、 、g 、 r / 怠 鸯 n Z U.S. PatentUS 8,052,085 B2Nov. 8, 2011Sheet 6 of 8q I虑 T 平 I i IIT丿 寸IIA、n A沁a7 0g 沁、类汰、沟:g | 0g / 05l 甘 I 气 I I I I 1 I 归 / /, 刀刀I I 1 1 11 1 1 1 1II-7 1 L - 1 ) ( L 1 I 1,11 三l ljl i 、 , I-/、j lj lIl gg - -l

26、L . 1 / 、 、-uj 0f 卜、z-、 -I 4 2恣/）$ ll 1 J V （ ,L l 1 、丿，、 / / - 、I Jll I I l 、 、 、 、二， 5 C I H 4. iI I f l i /文 支一、j 交j - l l l 、 44 4 II 、 、 0、二N 、1 11 gg 9、六头汰、汰汰三入U.S. PatentUS 8,052,085 B2Nov. 8, 2011Sheet 7 of 8g5 qZg 沪 勹Zg 、 r-、- 、./I I Ig 沁Vnt I,I阳7 沁f 沁U.S. PatentUS 8,052,085 B2Nov. 8, 2011S

27、heet 8 of 8翎Zg 沁BTI 05 、A AAgQ ag 、a US 8,052,085 B22 1 THRUST REVERSER FORA TURBOFAN GAS TURBINE ENGINETECHNICAL HELDThe invention relates to thrust reversers for turbofan gas turbine engines.BACKGROUNDFIG. 4 is a schematic longitudinal cross-sectional view showing an example of the improved arrang

28、ement with the thrust reverser doors in the stowed position;FIG. 5 is a view similar to FIG. 4, showing the doors in a5 deployed position;FIG. 6 is an isometric view showing an ex 皿 ple of an improved upper door;FIG. 7 is an isometric view showing an ex 皿 ple of an improved lower door;10 FIG. 8 is a

29、 cross-section through lines 8-8 of FIG. 1;FIG. 10 is a view similar to FIG. 4, showing anotherThrust reversers on gas turbine engines have to fulfill twoIG. 9 i _an_ ometric_ view_ of the upper se?l shown)n functions: while stowed, to provide an exhaust nozzle for the FIG. 4 and FIG. 9B is an enlar

30、ged cross section of an ex皿 ple direct thrust generated by the engine; and while deployed, to of the seal mounted to the jet pipe; andredirect the engine thrust to order to provide a deceleratingforce after landing. Since almost the enti.re flight sequence occurs with the thrust reverser in the stow

31、ed position, it is desirable that the presence of the thrust reverser does not15 embodiment ofthe improved arrangement.DETAILED DESCRIPTIONdegrade the direct thrust performance of the engineReferring now to FIG. 1, there is shown an ex 皿 ple of a While many thrust reversers models have been used suc

32、- 20 nacelle 20 including a thrust reverser 22 of the target/bucketcessfully for a number of years, there is a need to provide antype, located in the aft section 20a of the nacelle 20. The improved arrangement.turbofan gas turbine engine is located within the nacelle 20 and the engine and nacelle 20

33、 are attached under the wings, orSUMMARYto the fuselage, of the aircraft using an appropriate arrange-25 ment (not shown).In one aspect, the present concept provides athrust reverserThe thrust reverser 22 comprises two opposite pivoting for a turbofan engine, the thrust reverser comprising at least

34、doors 24, 26 forming an exhaust exit nozzle of the nacelle 20, first and second doors pivotally connected to a jet pipe, the jet having a planar exit 28, when the doors are in their stowed pipe having an exit defined by an exit profile, each door position. One door 24 is at the upper side and the ot

35、her door having an outer skin and an inner skin mounted to the outer 30 26 is at the lower side.如 n, the inner skin extending along only a portion of an axialEach door 24, 26 has a trailing edge 24a, 26a defining alength of the outer skin, the inner skin of the doors havingportion of the exit 28. Th

36、e arrows in FIG. 1 represent the edges that matingly engage the edges of the jet pipe substan-direct thrust air flow generated by operation of the engine tially along the length of the exit profile.FIG. 2 is an enlarged view of only the thrust reverser ofIn another aspect, the present concept provid

37、es a thrust 35 FIG. 1, showing a jet pipe 30 to which doors 24, 26 are reverser comprising: a jet pipe having an inner flow surfacepivotally connectedfor receiving engine exhaust gases, the jet pipe having aFIG. 3 is a rear view of what is shown in FIG. 2. The doorscircular portion and two arms exte

38、nding rearward of the cir- 24, 26 are in their deployed pos 山 on in FIGS. 2 and 3. The jet cular portion; and a pair of opposed doors pivotally connected pipe 30 is concealed inside the aft section 20a of the nacelle to the jet pipe arms, each door having an inner flow surface in 40 20 when the door

39、s 24, 26 are in their stowed position, as in registry with the inner flow surface of the jet pipe and mating FIG. 1therewith to engage the jet pipe along its exit length when theAs shown in FIG. 4, the jet pipe 30 has axially-down- doors are closed, wherein the inner surface of the jet pipe andstrea

40、m-extending arms 32 on either side of upper and lower the inner surfaces of the doors co-operate to provide a nozzlecutouts 34, with peripheral edges defining the cutouts 34, for engine exhaust gases.45 each edge having substantially horizontal or longitudinal por- In another aspect, the present con

41、cept provides a thrusttion 38 and a generally vertical or circumferential portion 40 reverser for a turbofan engine, the thrust reverser comprising(which the reader will appreciate is semi-circular in shape, an interior wall defining a continuous nozzleinterior surfaceextending from the substantiall

42、y horizontal portion 38 on one from a nozzle inlet to a thrust reverser exit when the doors areside or arm of the jet pipe 30, to the substantially horizontal in a stowed position, the nozzle interior surface co-opera- so portion 38 on the other side or arm of the jet pipe 30). Periph- tively define

43、d by an internal surface of a jet pipe of the thrusteral edges preferably include a seal 52 along the lengths ofreverser, internal surfaces of a plurality of closed thrustportions 38 and 40, as will be described further below reverser doors of the thrust reverser, and seals extendingThe arrows in FI

44、G. 2 indicate the main exhaust gas flow between the jet pipe and each door substantially along anpath during thrust reversal. Exhaust gases coming out of the interface between the jet pipe and said door.55 engine are redirected substantially forwardly when thedoorsFurther details of these and other

45、aspects of the improve-24, 26 are in their deployed position.ments presented herein will be apparent from the detailedThe gases exit the doors 24, 26 in the vicinity of the订description and appended figures.leading edges 24b, 26b. The leading edges 24b, 26b arelocated at the front of the doors 24, 26

46、, and hence are ?lead- BRIEF DESCRIPTION OF THE FIGURES60 ing? edges with reference to the travel path of the aircraft.The redirection of the gases coming out of the engineFIG. 1 is a side view of an ex 皿 ple of a nacelle provided creates a horizontal retarding force opposing the forward with a thru

47、st reverser according to the present arrangement, movement of the aircraft. Increasing the output thrust gener - its doors being shown in a stowed position;ated by the engine increases the aerodynamic deceleratingFIG. 2 is a schematic side view of the thrust reverserofFIG. 65 force.1, with doors sho

48、wn in a deployed position;In the illustrated exaniple, the trailing edge 24a of the FIG. 3 is a rear view of what is shown in FIG. 2;upper door 24 is pivoted behind the trailing edge 26a of the4 3 US 8,052,085 B2lower door 26, this resulting from the asy=etrical position-deflectors 50, if required o

49、r desired, for example to stiffen ing of thepivotswithreferencetothehorizontal medial planeskin 44 or structurally support flow deflector 50of the jet pipe 30, as described in applicants co-pendingReferring to FIG. 8, shown is a schematic lateral cross- application Ser. No. 11/534,202, filed Sep. 21, 2006.section of the thrust reverser, taken generally along the lines It should be noted that, although the doors 24, 26 are 5 8-8 in FIG. 1 (door