3-篩選及標(biāo)引后的專利著錄項(xiàng)目數(shù)據(jù)及專利全文us8776527b1_W

1、US008776527B1(12) United States Patent(io) Patent No.:US 8,776,527 B1Sokhey et al.(45) Date of Patent:Jul. 15, 2014(54) TECHNIQUES TO REDUCE INFRARED3,938,742 A *2/1976 Corson, Jr239/265.11DETECTION OF A GAS TURBINE ENGINE4,077,206 A3/1978 Ayyagari4,175,640 A11/1979 Birch etal.4,214,441 A *7/1980 Mo

2、uritsen et al60/262(75) Inventors: Jagdish Sokhey, Indianapolis, IN (US);4,240,519 A12/1980 WynoskyBrian Kornegay, Indianapolis, IN (US)4,295,332 A10/1981 Steyer et al.4,372,110 A *2/1983 Cheng et al60/262(73) Assignee: Rolls-Royce North American4,543,784 A10/1985 Kirker Technologies, Inc., Indianap

3、olis, IN4,576,002 A3/1986 Mavrocostas (US)4,577,462 A3/1986 Robertson5,269,132 A12/1993 Loucks5,344,102 A *9/1994 Nakadate et al244/35 R( * ) Notice:Subject to any disclaimer, the term ofthis5,722,233 A3/1998 Nikkanen et al.patent is extended or adjusted under 355,769,317 A6/1998 Sokhey et al.U.S.C.

4、 154(b) by 1104 days.6,105,901 A8/2000 Ulanoski 6,606,854 B18/2003 Siefker et al. 7,178,338 B22/2007 Whurr(21) Appl.No.: 12/214,2692002/0178711 Al12/2002 Martens2004/0068981 Al*4/2004 Siefker et al60/262(22) Filed:Jun. 17, 20082004/0074224 Al4/2004 Hebert(Under 37 CFR 1.47)2004/0083713 Al5/2004 Clar

5、k2005/0081509 Al*4/2005 Johnson60/226.1(51) Int.Cl.2010/0146980 Al*6/2010 Strom et al60/770F02K1/82(2006.01)* cited by examinerF02K1/S2(2006.01)F02K1/04(2006.01)Primary Examiner Andrew Nguyen(52) U.S. Cl. (74) Attorney, Agent, or Firm Krieg DeVault LLP USPC60/770(58) Field of Classification Search(5

6、7)ABSTRACTUSPC . 60/264, 770, 39.5, 761-766; 181/213,A discharge nozzle is provided having a centerbody and a 181/220; 239/265.17, 265.19, 127.3conduit enclosing the centerbody and is operable to receiveSee application file for complete search history.exhaust flow from a turbine discharge ofa gas tu

7、rbine engine.In one form the centerbody is symmetric and extends along(56)References Citedthe flow direction, rising away from a reference axis to aU.S. PATENT DOCUMENTSmaximum position before falling and converging on the reference axis. A set ofrings is disposed between the centerbody3,048,376A *

8、8/1962 Howaldetal. 366/262and the conduit and are positioned between the centerbody3,670,501A * 6/1972 Arand . 60/763and the conduit.3,673,803A7/1972 Macdonald3,701,255A * 10/1972 Markowski . 60/76228 Claims, 6 Drawing Sheets57U.S. PatentJul. 15, 2014Sheet 1 of 6US 8,776,527 B1% T R 1, AgiO RFI RPU.

9、S. PatentJul. 15, 2014Sheet 2 of 6US 8,776,527 B12.ig FtOU.S. PatentJul. 15, 2014Sheet 3 of 6US 8,776,527 B13.gi FU.S. PatentJul. 15, 2014Sheet 4 of 6US 8,776,527 B14.gi Fc 011U.S. PatentJul. 15, 2014Sheet 5 of 6US 8,776,527 B1U.S. PatentJul. 15, 2014Sheet 6 of 6US 8,776,527 B1OUS 8,116,.527 B112TEC

10、HNIQUES TO REDUCE INFRAREDpart of the exhaust stream may be received by a dischargeDETECTION OF A GAS TURBINE ENGINEnozzle 54 which acts to reduce and/or block the emission ofinfraredradiation from the gas turbine engine 52. By reducingBACKGROUNDand/or blocking emission of infrared radiation, the di

11、scharge5 nozzle 54 assists in thwarting infrared detection devices used The present invention generally relates to gas turbinein certain anti-aircraft weapons. As used herein, the term engine exhausts, and more particularly, but not exclusively, to“aircraft” includes, but is not limited to, helicopt

12、ers, airplanes, unmanned space vehicles, satellites, fixed wingdevices used in gas turbine engine exhausts. Gas turbine vehicles, variable wing vehicles, rotary wing vehicles, hoverengines operate in a variety of conditions and produce crafts, and other airborne and/or extraterrestrial (spacecraft)

13、exhaust flow at a variety ofmass flow rates, temperatures, and 10 vehicles. Further, the present inventions are contemplated for pressures. The exhaust flow and components of the gas tur utilization in other applications that may not be coupled with bine engine may produce a distinct thermal signatu

14、re whenan aircraft such as, for example, industrial applications, the gas turbine engine is operating. Blocking the view of anpower generation, pumping sets, naval propulsion, weapon external observer into a hot section of a gas turbine enginesystems, security systems, perimeter defense/security sys

15、 remains an area of interest. Unfortunately, some existing 15 tems, and the like known to one of ordinary skill in the art. systems often fall short of desired performance relative toThe discharge nozzle 54 may be used with many different certain applications. Accordingly, there remains a need foren

16、gine types. For example, though the gas turbine engine 52 further contributions in this area oftechnology.is depicted in FIG. 1 as a turboprop engine, other types ofgasturbine engines may also be used such as turbojets, turbofans,SUMMARY20 turboshafts, ramjets, and scramjets, to set forth just a few

17、 non-limiting examples. In addition, the discharge nozzle 54One embodiment of the present invention includes a may be used in other types of internal combustion engines unique infrared signature suppression technique for gas tur such as the reciprocating engine variety. Hybrid engines are bine engin

18、es. Other embodiments include unique methods, also contemplated herein.systems, devices, and apparatus involving the reduction of 25Referring to FIG. 2, one embodiment of the dischargedetectable infrared radiation from a gas turbine engine. Fur nozzle 54 is shown within an aircraft nacelle 57. The a

19、ircraft ther embodiments, forms, features, aspects, benefits, and nacelle 57 is used to enclose the gas turbine engine 52 and at advantages of the present application shall become apparent least part of the discharge nozzle 54 and assists in reducing from the description and figures provided herewit

20、h.aircraft drag. The nacelle 57 in the illustrative embodiment30 may be replaced with any suitable aircraft structure, if necBRIEF DESCRIPTION OF THE DRAWINGSessary, to enclose the discharge nozzle 54. The dischargenozzle 54 is oriented downstream ofa turbine 59 and a turbine FIG. 1 is a diagrammati

21、c view of a vehicle with a gasdischarge 61.turbine engine serving as prime mover.The discharge nozzle 54 includes a centerbody 58, a con FIG. 2 is a partial schematic, side sectional view of one 35 duit 60, a passage 62 between the centerbody 58 and the type of discharge subsystem to reduce detectio

22、n of infraredconduit 60, a diffuser 64, rings 66, struts 68 and the mixer 56. radiation through an outlet of the gas turbine engine.The centerbody 58 includes an upstream side 70, an apex 72, FIG. 3 is a partial schematic, side sectional view ofanotherand a downstream side 74 and in one form is a bo

23、dy of type of discharge subsystem to reduce detection of infraredrevolution about an axis, such as the reference axis L in the radiation through an outlet of the gas turbine engine.40 illustrative embodiment. The centerbody 58 also includes FIG. 4 is a partial schematic, side sectional view of still

24、cooling slots 76 which may emit a fluid 77 such as ambient another type of discharge subsystem to reduce detection ofair, or air from a compressor ofthe gas turbine engine 52, to infrared radiation through an outlet ofthe gas turbine engine.set forth just two non-limiting examples. In the illustrati

25、ve FIG. 5 is a partial schematic, side sectional view of yetembodiments, the centerbody 58 is symmetric about the ref another type of discharge subsystem to reduce detection of 45 erence axis L, while in other embodiments the centerbody 58 infrared radiation through an outlet ofthe gas turbine engin

26、e.may be non-symmetrical. In addition, though the centerbody FIG. 6 is a partial schematic, side sectional view of a58 is centered about the reference axis L, in some embodi further type of discharge subsystem to reduce detection ofments the centerbody 58 may not be centered about the axis L. infrar

27、ed radiation through an outlet ofthe gas turbine engine.The centerbody 58 extends from the turbine discharge 61 to a50 termination point 82. In some embodiments the centerbodyDETAILED DESCRIPTION OF58 may extend from a point or structure other than the turbine REPRESENTATIVE EMBODIMENTSdischarge 61.

28、 The termination point 82 may be upstream,coincident with, or downstream ofeither the conduit 60 or the For the purposes of promoting an understanding of themixer 56.principles ofthe invention, reference will now be made to the 55The upstream side 70 extends along the reference axis L embodiments il

29、lustrated in the drawings and specific lanapproximately from the turbine discharge 61 to the apex 72. guage will be used to describe the same. It will neverthelessIn some embodiments, the upstream side 70 may extend from be understood that no limitation ofthe scope ofthe inventiona point or structur

30、e other than a turbine discharge. The is thereby intended. Any alterations and further modificationsupstream side 70 is spaced a distance 78 from the axis L in the described embodiments, and any further applications of 60 which remains substantially constant until the upstream side the principles of

31、 the invention as described herein are con70 reaches a point 80, where it then enters an area character templated as would normally occur to one skilled in the art toized by an increase in the distance 78. In some embodiments, which the invention relates.the upstream side 70 may have a portion or po

32、rtions that are Turning now to FIG. 1, shown is an aircraft 50 having a gasnot at a substantially constant distance 78 from the reference turbine engine 52 used as a source of propulsion. The gas 65 axis L between the turbine discharge 61 and the point 80. For turbine engine 52 produces an exhaust s

33、tream at elevatedexample, some embodiments of the upstream side 70 may temperatures caused at least by a combustion process. At leasthave an increasing distance 78 just upstream ofthe point 80.US 8,116,.527 B134As the upstream side 70 continues to extend along the referany point in between. The apex

34、 88 ofthe illustrativeembodi ence axis L from the point 80 it also continues to increase inment is upstream of the apex 72, but in some embodiments distance 78 until it reaches the apex 72, or an area near themay be at the same or downstream position as the apex 72. apex 72. The shape ofthe upstream

35、 side 70 between the pointThe downstream side 90 begins at or near the apex 88 and 80 and the apex 72 may be any suitable shape, including a 5 continues to the mixer 56, ifpresent. The downstream side 90straight line. The shape may also have smoothed transitionsmay extend in a straight line or may t

36、ake on any other shape around the point 80 and the apex 72 ifnecessary for fluid flowin other embodiments.or other considerations.The passage 62 is formed between the conduit 60 and theThe apex 72 is the point on the centerbody 58 furthest fromcenterbody 58 and is annular in shape. Some embodiments,

37、 the reference axis L. In some embodiments, the centerbody 10 however, may only be partially annular in shape. The passagea 58 may not have a well-defined apex 72, in which case an62 includes a hub side 92 and a tip side 94 and has a crossrbitrary point can be selected as the apex. For example, thec

38、enterbody 58 may have a flat top surface that is parallel to thesectional area that can be constant along portions ofits length.reference axis L. In this case, the apex 72 may be chosen as anIn some portions of the passage 62, the cross sectional areaupstream edge of the flat surface, a downstream e

39、dge of the 15 may increase. For example, as the passage 62 extends from flat surface, or any point in between.the turbine discharge 61 it may have an increase in cross The downstream side 74 begins at or near the apex 72 andsectional as it approaches one or more of the rings 66. In continues to the

40、termination point 82. The downstream sideaddition, in some embodiments the cross sectional area may74 may extend in a straight line or may take on any otheralso increase in cross sectional area in a portion upstream ofshape in other embodiments.20 the mixer 56.The cooling slots 76 are formed around

41、the circumferentialThe diffuser 64 includes an area within the passage 62 periphery of the centerbody 58 in the illustrative embodi downstream ofthe apex 72 ofthe centerbody 58 characterized ment, but in other embodiments may be formed only partially by an increase in cross sectional area. In some e

42、mbodiments around the periphery. Some embodiments may include fewer the diffuser 64 may be included upstream of the apex 72, cooling slots 76 than the illustrative embodiment, while other 25 while in other embodiments the diffuser 64 may not be embodiments may include more cooling slots 76. Though t

43、he present at all.illustrative embodiment depicts a cooling slot 76 formed atThe rings 66 are disposed upstream of the apex 72 in the the apex 72 and at a location downstream from the apex 72,illustrative embodiment and are annular in shape and act in the cooling slots 76 may be formed in any locati

44、on of theconjunction with the centerbody 58 to block the view of the centerbody 58 in other embodiments.30 turbine 59 from an outside observer. Though threerings 66a, The conduit 60 encloses the centerbody 58 and extends66b, and 66c are depicted in the illustrative embodiment, along the reference ax

45、is L. The conduit 60 includes another embodiments may include fewer rings or more rings. upstream side 86, an apex 88, and a downstream side 90.Each of the rings 66 includes an airfoil cross sectional shape Much like the centerbody 58 in the illustrative embodiment,96a, 96b, and 96c. In addition, th

46、e rings 66 are symmetric and the conduit 60 is centered about the reference axis L, but in 35 each are centered about the axis L, though some embodiments some embodiments may not be centered. In addition, themay be non-symmetric and others may additionally and/or conduit 60 is depicted as symmetrica

47、l but in some embodialternatively not be centered about the axis L. Each ring 66a, ments may be non-symmetrical. The conduit 60 extends from66b, and 66c has an annular diameter 61a, 61b, and 61c, the turbine discharge 61 to the mixer 56. In some embodirespectively, as measured between the upstream e

48、dge ofeach ments, the conduit 60 may extend from structures or points 40 of the individual ring 66c, 66b, and 66c. In one form the other than the turbine discharge 61. In still further embodidiameters 61a, 61b, and 67c are perpendicular to the axis L, ments, the mixer 56 may not be present such that

49、 the conduitbut need not be in all embodiments. The rings 66a, 66b, and 60 includes a termination point. In any event, the conduit 6066c may be spaced apart from one another to maintain a may extend to a point that is at the same axial location ofthesubstantially constant inter-ring distance along t

50、he axis L to termination point 82 of the centerbody 58, or may be 45 assist in minimizing and/or eliminating a cross sectional area upstream or downstream of the termination point 82.constriction between the rings. Some embodiments may have The upstream side 86 of the conduit 60 extends along thea v

51、ariable cross sectional area between the rings along the reference axis L from the turbine discharge 61 to the apex 88.axis L. In still further embodiments, the cross sectional area In some embodiments, the upstream side 86 may extend frommay increase or decrease. The rings 66 may be stacked one a p

52、oint or structure other than a turbine discharge. The 50 inside the other because the rings may have unique diameters. upstream side 86 is spaced a distance 84 from the axis LUsually one of the rings 66 has a largest diameter which which in the illustrative embodiment increases from the turallows ot

53、her ofthe rings 66 to be stacked or placed inside the bine discharge 61 to the apex 88. In some embodiments,largest diameter ring, whether the other rings are locatedhowever, the conduit 60 may have a portion or portions thatupstream or downstream of the greatest diameter ring.extend at a constant d

54、istance 84 or a decreasing distance 84. 55The leading edges and trailing edges of the rings 66 are As the upstream side 86 extends along the reference axis L itaxially displaced relative to each other. For example, the rises away from the reference axis L until it reachesthe apexleading edge ofthe r

55、ing 66a is upstream ofthe leading edge of 88, or an area near the apex 88. The shape ofthe upstream sidethe ring 66b, which is upstream ofthe leading edge ofthe ring 86 between the turbine discharge 61 and the apex 88 may be66c. The same is true for the trailing edges. In some embodi any suitable sh

56、ape, including a straight line.60 ments, the leading and trailing edges of the rings 66a, 66b,The apex 88 is the point on the conduit 60 furthest from the and 66c may be axially displaced according to another rela reference axis L. In some embodiments, the conduit 60 may tionship. For example, the leading edge ofthe ring 66 a may be not have a well-defined apex 88, in which case an arbitrary downstrea