(12) Ulllted States Patent
`Norris et al.
`
`(10) Patent No.:
`(45) Date of Patent:
`
`US 7,966,807 B2
`Jun. 28, 2011
`
`US007966807B2
`
`(54) VAPOR (TOOLED STATIC TURBINE
`HARD\vARE
`
`(75)
`
`.
`.
`..
`Inventors: James w. Norris. Lebanon. L 1 (U5):
`James D. Hill. Tolland. CT (US); Craig
`A. Nordeen. Manchester. (‘T (US)
`
`(73) Assignee: United Technologies Corporation.
`Hartford. CT (US)
`
`( * ) Notice:
`
`Subject to anv disclaimer. the term of this
`patent is extended or adjusted under 35
`U.S.(‘. 154(b) by 1423 days.
`(21) App]. N01; 1]/554.472
`
`8.-I967 Burggrafetal.
`3.334.685 A
`10.1974 Grondahl ct al.
`3.844.679 A
`1.11999 Stickler etal.
`5.857.836 A
`9.11999 S ' ‘kl
`.1.
`5.954.478 A
`11,199., L'1‘,;,c:’,§ue1§1"c,a1V ......... N 415,114
`51975341 A ..
`3,3005 Jones
`519311334 33
`1.-2006 Venkatai-amani et al.
`6.990.797 B2
`7.2010 Norris et al.
`.................. .. 601247
`7.748.211 B2 “
`23007 H°"°W“y elal‘
`300770023732 Al
`FOREIGN PATENT DOCUMENTS
`
`83005
`W0 W0 2005073539 Al
`OTHER PUBI.ICATIONS
`K R
`S N
`"whm ,
`H m P_
`7" mp
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`IS 3
`E
`IPC.
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`chcresourees.com1‘htpipes.shtml (visited Oct. 2. 2006).
`
`arayanan
`
`.,
`
`i'1“\VW'\\’.
`
`(22)
`
`Filed:
`
`Jan. 17, 2007
`
`* ‘’‘‘‘’d by e"“’“‘“’*”
`
`(65)
`
`Prior Publication Data
`US 2010/0263388 A1
`Oct. 21. 2010
`
`Louis Casaregola
`Primary Examiner
`(74) Atrornqv, Agent, or Firm Kinney & Lange. P..-\.
`
`(51)
`
`Int. Cl.
`(200001)
`[:02]; 3/02
`(2()()(,_()])
`[«'02(‘ 7/12
`60/226.1: 60/8062415/114
`(52) U.S. Cl.
`(58) Field of Classification Search ............. .. 60/39.511.
`60/2261 3061 415/114‘ 177‘ 173‘ 179
`gee am-,]iCa1i0n me for c0mp1e1e Search 111510,-y,
`
`(56)
`
`References Cited
`
`2.708.564 A "‘
`3.287.906 A "‘
`
`531955 Erickson ..................... .. 415.1114
`ll.'l966 .VleCor1nack ............ .. 60-39.511
`
`(57)
`
`ABSTRACT
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`_
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`1
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`A cooling system tor a gasttirtnne engine mcltides a non-
`rotating coniponenl extending‘ into an engine llowpath. a
`Vapor cooling asscu_1b1y_ C011h%}1|'°d 10 Imnsport
`tllcnnal
`energy fmm_3 V3p‘mZ3"_°“ Seem“ 1° 3 °‘7“de“_Ser Secllm
`tlirongh cyclical evaporation and condensanon ot a working
`inediuin sealed within the vapor cooling asseinbly. wherein
`the vaporization section is located at least partially within the
`non-rotating component. and wherein the condenser section
`is located outside the non-rotating component and away from
`the engine flgvvpath.
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`20 Claims, 2 Drawing Sheets
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`10
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`UTC-2006.001
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`GE v. UTC
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`Trial IPR2016-00534
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`

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`9.8.N3.N
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`CL
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`FIG. 2
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`US 7,966,807 B2
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`1
`VAPOR COOLED STATIC TURBINE
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`HARDWARE
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`BACKGROUND OF THE INVENTION
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`The present invention relates to a system for cooling static
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`structures of gas turbine engines.
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`Known gas turbine engines have utilized superalloys, ther-
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`mal barrier coatings (TBCs), and fluidic cooling schemes in
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`order to provide engine structures that can operate efficiently
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`at high temperatures and pressures while still maintaining a
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`relatively long lifespan. However, it is desired to provide
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`improved cooling capabilities for gas turbine engines, in
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`order to better maintain engine components at temperatures
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`below designated maximum operating temperature levels.
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`Moreover, it is desired to reduce energy losses by permitting
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`thrust recovery ofthermal energy transferred away from a gas
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`flowpath by a cooling system.
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`BRIEF SUMMARY OF THE INVENTION
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`A cooling system for a gas turbine engine according to the
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`present invention includes a non-rotating component extend-
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`ing into an engine flowpath, a vapor cooling assembly con-
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`figured to transport thermal energy from a vaporization sec-
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`tion to a condenser section through cyclical evaporation and
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`condensation of a working medium sealed within the vapor
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`cooling assembly, wherein the vaporization section is located
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`at least partially within the non-rotating component, and
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`wherein the condenser section is located outside the non-
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`rotating component and away from the engine flowpath.
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`BRIEF DESCRIPTION OF THE DRAWINGS
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`FIG. 1 is a schematic view of a gas turbine engine having a
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`vapor cooling assembly according to the present invention.
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`FIG. 2 is a schematic view of a portion of the gas turbine
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`engine of FIG. 1.
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`DETAILED DESCRIPTION
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`In general, the present invention relates to a gas turbine
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`engine that utilizes a vapor cooling assembly to cool non-
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`rotating structures that extend into a gas flowpath (typically a
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`combustion or turbine flowpath). The vapor cooling assembly
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`includes a vaporization section located at
`least partially
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`within a static structure that is exposed to a gas flowpath from
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`which it is desired to remove thermal energy, and a condenser
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`section located adjacent to or spaced from the gas flowpath
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`where it is desired to expel thermal energy. The vapor cooling
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`assembly is configured to transport thermal energy from the
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`vaporization section to the condenser section at a relatively
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`high rate through cyclical evaporation and condensation of a
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`working medium sealed within the vapor cooling assembly.
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`The condenser section can expel thermal energy to a fan
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`bypass stream located adjacent to the combustion gas flow-
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`path, in order to permit thrust recovery ofthat thermal energy
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`in the fan bypass stream. A flow guide structure can be used to
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`direct fan bypass air toward and past the condenser section.
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`As used herein, the term “static” as applied to gas turbine
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`engine parts generally refers to non-rotating parts, although
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`such parts may be subject to some movement, for instance,
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`when installed in an engine of a movable vehicle.
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`FIG. 1 is a schematic view of a dual-spool gas turbine
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`engine 10 that includes a fan section 12, a low-pressure com-
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`pressor section 14, a high-pressure compressor section 16, a
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`combustor section 18, a high-pressure turbine section 20, a
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`low-pressure turbine section 22, and a fan bypass duct 24. A
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`centerline CL is defined by the engine 10. The illustrated
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`embodiment of the gas turbine engine 10 is provided merely
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`by way of example, and it should be recognized that the
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`present invention applies to gas turbine engines of any con-
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`figuration. Those of ordinary skill in the art will understand
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`the basic operation of gas turbine engines, and therefore fur-
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`ther discussion here is unnecessary.
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`The engine 10 further includes a vapor cooling assembly
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`26 located at the low-pressure turbine section 22. FIG. 2 is an
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`enlarged schematic view of a portion ofthe gas turbine engine
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`10, showing the vapor cooling assembly 26 in greater detail.
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`As shown in FIG. 2, a gas flowpath (e.g., combustion of
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`turbine flowpath) is defined between a first boundary wall 28
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`and a second boundary wall 30. A fan bypass flowpath is
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`defined by the fan bypass duct 24. Gas in the fan bypass
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`flowpath is generally at a lower temperature and pressure than
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`gas in the combustion gas flowpath. The illustrated embodi-
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`ment of the engine 10 shows the second boundary wall 30
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`forming a boundary of both the combustion gas flowpath and
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`the fan bypass duct 24. However, the combustion gas flow-
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`path and the bypass duct 24 can be spaced apart in alternative
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`embodiments.
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`An airfoil-shaped vane 32 of a stator assembly at the low-
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`pressure turbine section 22 extends into the combustion flow-
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`path. The vane 32 is a static component of the gas turbine
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`engine 10. In an alternative embodiment, the structure desig-
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`nated by reference number 32 in FIG. 2 could represent a
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`strut.
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`The vapor cooling assembly 26 includes a vaporization
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`section 34 that extends into the vane 32 and a condenser
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`section 36 that is located away from the combustion gas
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`flowpath. The condenser section 36 extends either fully or at
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`least partially into the fan bypass duct 24 (or other suitable
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`area, e.g., one in which the vapor can be cooled) and an
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`optional flow guide 38 directs fan bypass air toward and along
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`the condenser section 36. Air passing along the condenser
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`section 36 absorbs thermal energy expelled from the vapor
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`cooling assembly 26. It should be recognized that the particu-
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`lar size and shape of the vaporization section 34, and its
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`particular location within the vane 32 can vary as desired.
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`Likewise, the particular configuration of the condenser sec-
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`tion 36 can vary as desired.
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`The engine 10 includes a plurality of vanes arranged in an
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`annular configuration about
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`In one
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`embodiment, each vane ofa particular stage is configured like
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`vane 32, as shown in FIG. 2. That is, each vane 32 has a
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`dedicated vapor cooling assembly 26, and a number of dis-
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`crete condenser sections 36 extend into the fan bypass duct
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`24. In alternative embodiments, the vapor cooling assembly
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`26 provides cooling to a number of different structures of the
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`engine 10. For example, nozzle segments that each include
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`two or more airfoil shaped vanes could utilize a common,
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`shared condenser section 36 with separate vaporization sec-
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`tions 34 that extend into each vane 32 of the nozzle.
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`The vapor cooling assembly 26 is sealed, and contains a
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`working medium. The vapor cooling assembly 26 functions
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`as a heat pipe that uses an evaporative cooling cycle to transfer
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`thermal energy through the evaporation and condensation of
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`a working medium. In particular, the vapor cooling assembly
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`26 utilizes an evaporative cooling cycle to transfer thermal
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`energy from the vane 32 to air passing through the fan bypass
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`duct 24. Thermal energy absorbed by the vane 32 from the hot
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`gases in the combustion gas flowpath heats the vaporization
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`section 34, which causes the working medium in the vapor-
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`ization section 34 to evaporate. Moreover, the relatively cool
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`air in the fan bypass flowpath absorbs thermal energy from the
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`UTC-2006.004
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`UTC-2006.004
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`

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`4
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`US 7,966,807 B2
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`3
`condenser section 36, and causes the (vaporized) working
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`medium to condense. The working medium physically moves
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`between the vaporization section 34 and the condenser sec-
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`tion 36, in order to transfer the thermal energy between the
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`locations where evaporation and condensation occur. Con-
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`ventional capillary action structures (e.g., wicking structures)
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`or a capillary action foam are included inside the vapor cool-
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`ing assembly 26 in order to facilitate desired movement ofthe
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`working medium along an established path between the con-
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`denser section 36 and the vaporization section 34 in a well-
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`known manner without requiring the aid of gravity or other
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`orientation-specific limits.
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`The composition of the working medium used in the vapor
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`cooling assembly 26 is selected according to the particular
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`operating conditions at which heat transfer is desired. Typi-
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`cally, working media conventionally used with evaporative
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`cooling cycles are dependent upon operation within a particu-
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`lar range of temperature conditions (as well as pressure con-
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`ditions). It is therefore necessary to select a suitable working
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`medium based on the particular conditions under which each
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`of the vapor cooling assembly is expected to operate, as will
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`be understood by those skilled in the art. Temperatures in
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`typical gas turbine engines can reach l,649° C. (3,000° F.) or
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`more, although actual engine temperatures will vary for dif-
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`ferent applications, and under different operating conditions.
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`For instance, while the vapor cooling assembly 26 is opera-
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`tional, the engine 10 is configured such that the average gas
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`flowpath temperature in will generally not exceed the maxi-
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`mum temperature limits for the materials (e.g., metals and
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`
`
`
`ceramics) used in and along the combustion gas flowpath. A
`
`
`
`
`
`
`
`
`
`
`non-exclusive list of possible working media is provided in
`
`
`
`
`
`
`
`
`
`Table 1, although those skilled in the art will recognize that
`
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`
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`
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`other working medium materials can be used.
`
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`
`
`TABLE 1
`
`
`
`
`
`
`Melting Point
`
`(° C.)
`
`
`-271
`
`-210
`
`-78
`
`-95
`
`-98
`
`-50
`
`-112
`0
`
`-95
`
`
`-39
`
`98
`179
`
`960
`
`
`
`
`
`Boiling Point
`
`
`(° C. at 101.3 kPa)
`
`
`
`
`-261
`
`-196
`
`-33
`57
`
`64
`
`76
`
`
`78
`
`100
`110
`
`
`361
`892
`
`1340
`
`2212
`
`
`
`
`
`
`
`
`Approximate
`
`Usefii Range
`
`
`(° C.)
`
`
`-271 o -269
`
`
`-203 o-160
`
`
`-60 o 100
`0 0120
`
`
`
`10 0130
`
`
`
`10 o 160
`
`
`
`
`
`
`0 0130
`30 o 200
`
`
`
`50 o 200
`
`
`
`
`
`
`250 o 650
`600 01200
`
`
`
`1000 01800
`
`
`1800 o 2300
`
`
`
`
`
`
`
`
`
`
`
`Working
`
`Medium
`
`Helium
`
`Nitrogen
`
`Ammonia
`Acetone
`Methanol
`
`Flutec PP2 TM
`
`
`
`Ethanol
`Water
`
`Toluene
`
`
`Mercury
`Sodium
`Lithium
`
`Silver
`
`
`
`
`
`
`The optional flow guide 38 functions to direct air in the fan
`
`
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`
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`
`
`bypass flowpath toward and past the condenser section 36 of
`
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`
`
`the vapor cooling assembly 26, and can then direct air heated
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`
`
`by the condenser section 36 back to the fan bypass flowpath.
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`
`
`
`
`
`
`The flow guide 38 can be configured similarly to flow guides
`
`
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`
`
`
`
`
`used in conjunction with known heat exchangers. As shown in
`
`
`
`
`
`
`
`
`
`
`FIG. 2, the condenser section 36 is represented schematically
`
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`
`
`as a box within the throat of the flow guide 38. However, it
`
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`
`
`should be recognized that various embodiments ofthe present
`
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`
`
`
`invention can incorporate a condenser section 36 configured
`
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`
`
`with fins or other structures that span the throat of the flow
`
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`
`
`
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`
`
`guide 38, and have slots or passageways for air to flow
`
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`
`
`
`
`
`
`
`
`between those fins or other structures.
`
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`
`
`The vapor cooling assembly 26 can provide cooling to
`
`
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`
`
`
`
`static components of the engine 10, such as the vane 32, with
`
`
`
`
`
`
`
`
`
`
`
`
`essentially zero net energy loss, because the thermal energy
`
`
`
`
`
`
`
`
`
`
`10
`
`
`
`15
`
`
`
`20
`
`
`
`25
`
`
`
`30
`
`
`
`35
`
`
`
`40
`
`
`
`45
`
`
`
`50
`
`
`
`55
`
`
`
`60
`
`
`
`65
`
`
`
`transferred away from the combustion gas flowpath by the
`
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`
`
`vapor cooling assembly 26 is as air in the fan bypass flowpath
`
`
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`
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`
`
`gains thermal energy. Thermal energy added to air in the fan
`
`
`
`
`
`
`
`
`
`
`
`bypass flowpath raises the temperature and pressure of that
`
`
`
`
`
`
`
`
`
`air, which contributes to thrust output of the engine 10. The
`
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`
`
`
`
`
`
`
`
`
`flow guide 38 promotes efiicient flow of air along the con-
`
`
`
`
`
`
`
`
`
`
`denser section 36, and helps prevent aerodynamic efficiency
`
`
`
`
`
`
`
`losses in the fan bypass duct 24.
`
`
`
`
`
`
`
`The use of the vapor cooling assembly 26 of the present
`
`
`
`
`
`
`
`
`
`
`
`invention does not require the use of bleed air to achieve
`
`
`
`
`
`
`
`
`
`
`
`cooling of static engine components. The use of bleed air in
`
`
`
`
`
`
`
`
`
`
`
`prior art cooling system produces significant engine effi-
`
`
`
`
`
`
`
`ciency losses (e.g., in terms of thrust output or fuel burn
`
`
`
`
`
`
`
`
`
`
`efficiency). In that respect, the present invention provides a
`
`
`
`
`
`
`
`
`more efiicient cooling system.
`
`
`
`
`Although the present invention has been described with
`
`
`
`
`
`
`
`
`reference to preferred embodiments, workers skilled in the art
`
`
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`
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`
`
`will recognize that changes may be made in form and detail
`
`
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`
`
`
`without departing from the spirit and scope of the invention.
`
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`
`
`For instance, the system of the present invention can be used
`
`
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`
`
`
`
`to cool nearly any static component in nearly any location of
`
`
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`
`
`
`
`
`
`
`a gas turbine engine.
`
`
`
`
`What is claimed is:
`
`
`
`
`1. A system for an engine, the system comprising:
`
`
`
`
`
`
`
`
`
`a non-rotating component extending into an engine flow-
`
`
`
`
`
`
`
`path, wherein the engine flowpath is a gas turbine com-
`
`
`
`
`
`
`
`
`
`bustion flowpath;
`
`
`a vapor cooling assembly configured to transport thermal
`
`
`
`
`
`
`
`energy from a vaporization section to a condenser sec-
`
`
`
`
`
`
`
`tion through cyclical evaporation and condensation of a
`
`
`
`
`
`
`
`working medium sealed within the vapor cooling assem-
`
`
`
`
`
`
`
`bly, wherein the vaporization section is located at least
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`
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`
`
`partially within the non-rotating component to accept
`
`
`
`
`
`
`thermal energy from the non-rotating component, and
`
`
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`
`
`wherein the condenser section is located outside the
`
`
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`
`
`non-rotating component and away from the engine flow-
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`
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`
`
`
`path; and
`
`
`a fan bypass flowpath defined by boundary walls at a loca-
`
`
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`
`
`
`
`tion spaced from the engine flowpath, wherein the con-
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`
`
`denser section of the vapor cooling assembly is at least
`
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`
`
`partially exposed to the fan bypass flowpath such that
`
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`
`
`thermal energy is dissipated from the condenser section
`
`
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`
`
`to air in the fan bypass flowpath to raise a pressure of a
`
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`
`
`fluid in the fan bypass flowpath and contribute to thrust
`
`
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`
`
`production by the engine.
`
`
`
`
`2. The system of claim 1, wherein the non-rotating com-
`
`
`
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`
`
`
`ponent comprises a vane.
`
`
`
`3. The system of claim 1, wherein the non-rotating com-
`
`
`
`
`
`
`
`
`
`ponent comprises a support strut.
`
`
`
`
`4. A heat transfer system for use in a gas turbine engine, the
`
`
`
`
`
`
`
`
`
`
`
`system comprising:
`
`
`a turbine flowpath defined by at least one boundary wall;
`
`
`
`
`
`
`
`
`
`
`a non-rotating component that extends into the turbine
`
`
`
`
`
`
`
`flowpath;
`
`a vapor cooling assembly comprising:
`
`
`
`
`
`a vaporization section configured to accept thermal
`
`
`
`
`
`
`energy from the non-rotating component;
`
`
`
`
`
`a condenser section located outside the turbine flowpath;
`
`
`
`
`
`
`
`
`and
`
`a working medium sealed within the vapor cooling
`
`
`
`
`
`
`
`assembly, wherein cyclical evaporation and conden-
`
`
`
`
`
`sation of the working medium transports thermal
`
`
`
`
`
`
`
`energy from the vaporization section to the condenser
`
`
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`
`
`
`section; and
`
`
`a fan bypass flowpath defined by at least one duct wall,
`
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`
`wherein the condenser section of the vapor cooling
`
`
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`
`assembly is at least partially exposed to the fan bypass
`
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`
`
`UTC-2006.005
`
`UTC-2006.005
`
`

`
`
`
`US 7,966,807 B2
`
`
`
`
`
`
`
`
`
`
`5
`flowpath such that thermal energy is dissipated from the
`
`
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`
`
`condenser section to air in the fan bypass flowpath.
`
`
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`
`
`
`
`
`
`5. The system of claim 4, wherein the non-rotating com-
`
`
`
`
`
`
`
`
`
`ponent comprises a vane.
`
`
`
`6. The system of claim 4, wherein the non-rotating com-
`
`
`
`
`
`
`
`
`
`ponent comprises a support strut.
`
`
`
`
`7. The system of claim 4, wherein the vaporization section
`
`
`
`
`
`
`
`
`
`is located within the non-rotating component.
`
`
`
`
`
`
`8. A heat transfer system foruse in a gas turbine engine, the
`
`
`
`
`
`
`
`
`
`
`
`system comprising:
`
`
`a turbine flowpath defined by at least one boundary wall;
`
`
`
`
`
`
`
`
`
`
`a static component that extends into the turbine flowpath;
`
`
`
`
`
`
`
`
`
`a bypass flowpath defined by at least one bypass duct wall;
`
`
`
`
`
`
`
`
`
`
`
`and
`
`a vapor cooling assembly comprising:
`
`
`
`
`
`a vaporization section configured to accept thermal
`
`
`
`
`
`
`energy from the static component;
`
`
`
`
`
`a condenser section at least partially exposed to the
`
`
`
`
`
`
`
`
`
`bypass flowpath and configured to dissipate thermal
`
`
`
`
`
`
`
`energy to air in the bypass flowpath to provide thrust
`
`
`
`
`
`
`
`
`
`
`recovery; and
`
`
`a working medium sealed within the vapor cooling
`
`
`
`
`
`
`
`assembly, wherein cyclical evaporation and conden-
`
`
`
`
`
`sation of the working medium transports thermal
`
`
`
`
`
`
`
`energy from the vaporization section to the condenser
`
`
`
`
`
`
`
`
`section.
`
`9. The system of claim 8, wherein the static component
`
`
`
`
`
`
`
`
`
`comprises a vane.
`
`
`10. The system of claim 8, wherein the static component
`
`
`
`
`
`
`
`
`
`comprises a support strut.
`
`
`
`11. The system of claim 10, wherein fluid at the turbine
`
`
`
`
`
`
`
`
`
`
`flowpath adjacent to the vaporization section of the vapor
`
`
`
`
`
`
`
`
`
`
`
`
`
`
`
`
`
`
`
`
`10
`
`
`
`15
`
`
`
`20
`
`
`
`25
`
`
`30
`
`
`
`
`6
`cooling assembly is at a higher pressure than fluid at the
`
`
`
`
`
`
`
`
`
`
`bypass flowpath adjacent to the condenser section of the
`
`
`
`
`
`
`
`
`vapor cooling assembly.
`
`
`
`12. The system of claim 8, wherein the heat transfer system
`
`
`
`
`
`
`
`
`
`
`does not eject air into the bypass flowpath.
`
`
`
`
`
`
`
`
`13. The system ofclaim 8, wherein the vaporization section
`
`
`
`
`
`
`
`
`
`is located within the static component.
`
`
`
`
`
`
`14. The system of claim 8, wherein the bypass flowpath
`
`
`
`
`
`
`
`
`
`
`comprises a fan bypass flowpath.
`
`
`
`
`15. The system of claim 1 and further comprising:
`
`
`
`
`
`
`
`
`
`a flow guide positioned within the fan bypass flowpath to
`
`
`
`
`
`
`
`
`
`
`direct fan bypass air toward the condenser section ofthe
`
`
`
`
`
`
`
`
`
`
`vapor cooling assembly.
`
`
`
`16. The system of claim 15, wherein the flow guide is
`
`
`
`
`
`
`
`
`
`
`configured to direct fan bypass air along the condenser sec-
`
`
`
`
`
`
`
`
`
`tion of the vapor cooling assembly in a generally axial direc-
`
`
`
`
`
`
`
`
`
`tion.
`
`17. The system of claim 4 and further comprising:
`
`
`
`
`
`
`
`
`
`a flow guide positioned within the fan bypass flowpath to
`
`
`
`
`
`
`
`
`
`
`direct fan bypass air toward the condenser section ofthe
`
`
`
`
`
`
`
`
`
`
`vapor cooling assembly.
`
`
`
`18. The system of claim 17, wherein the flow guide is
`
`
`
`
`
`
`
`
`
`
`configured to direct fan bypass air along the condenser sec-
`
`
`
`
`
`
`
`
`
`tion of the vapor cooling assembly in a generally axial direc-
`
`
`
`
`
`
`
`
`
`tion.
`
`19. The system of claim 8 and further comprising:
`
`
`
`
`
`
`
`
`a flow guide positioned within the bypass flowpath to direct
`
`
`
`
`
`
`
`
`
`
`bypass air toward the condenser section of the vapor
`
`
`
`
`
`
`
`
`
`cooling assembly.
`
`
`20. The system of claim 19, wherein the flow guide is
`
`
`
`
`
`
`
`
`
`
`
`configured to direct bypass air along the condenser section of
`
`
`
`
`
`
`
`
`
`
`the vapor cooling assembly in a generally axial direction.
`
`
`
`
`
`
`
`
`*
`*
`*
`*
`*
`
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`
`
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`
`
`
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`
`
`
`
`
`
`
`
`UTC-2006.006
`
`UTC-2006.006