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Baffle for a Component of a Gas Turbine Engine

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Baffle for a Component of a Gas Turbine Engine (19) TZZ¥_Z__T (11) EP 3 170 981 A1 (12) EUROPEAN PATENT APPLICATION (43) Date of publication: (51) Int Cl.: 24.05.2017 Bulletin 2017/21 F01D 5/18 (2006.01) (21) Application number: 16200307.3 (22) Date of filing: 23.11.2016 (84) Designated Contracting States: (71) Applicant: United Technologies Corporation AL AT BE BG CH CY CZ DE DK EE ES FI FR GB Farmington, CT 06032 (US) GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR (72) Inventor: THORNTON, Lane Designated Extension States: Tolland, CT Connecticut 06084 (US) BA ME Designated Validation States: (74) Representative: Leckey, David Herbert MA MD Dehns St Bride’s House (30) Priority: 23.11.2015 US 201514948511 10 Salisbury Square London EC4Y 8JD (GB) (54) BAFFLE FOR A COMPONENT OF A GAS TURBINE ENGINE (57) An airfoil (60;160;260) according to an example (76) for conveying coolant (F). The baffle body (74) is of the present disclosure includes, an airfoil body (61) situated in the cavity (64,64A-C) such that a majority of defining a cavity (64,64A-C), and a externalbaffle surfaces of the sidewalls (78) abut the cavity (72,72’,72",72"’;172;272) including a baffle body (74) in- (64,64A-C). cluding sidewalls (78) and defining an internal passage EP 3 170 981 A1 Printed by Jouve, 75001 PARIS (FR) 1 EP 3 170 981 A1 2 Description rial. [0013] In a further embodiment of any of the foregoing BACKGROUND embodiments, the airfoil body extends between a plat- form and an airfoil tip. The cavity extends inwardly from [0001] This disclosure relates to cooling for a compo- 5 the airfoil tip, and the baffle body is situated in the cavity nent of a gas turbine engine. such that the internal passage is configured to eject cool- [0002] Gas turbine engines can include a fan for pro- ant adjacent the airfoil tip. pulsion air and to cool components. The fan also delivers [0014] A gas turbine engine according to an example air into a core engine where it is compressed. The com- of the present disclosure, and which the Applicant ex- pressed air is then delivered into a combustion section, 10 pressly reserves the right to claim, includes a rotor where it is mixed with fuel and ignited. The combustion spaced axially from a vane. At least one of the rotor and gas expands downstream over and drives turbine blades. the vane includes an airfoil body. The airfoil body includes Static vanes are positioned adjacent to the turbine blades external walls extending between a leading edge and a to control the flow of the products of combustion. The trailing edge, the external walls defining a cavity, and a blades and vanes are subject to extreme heat, and thus 15 baffle including a baffle body defining an internal passage cooling schemes are utilized for each. for conveying coolant. Sidewalls of the baffle body have a complementary geometry with the cavity. SUMMARY [0015] In an embodiment of the foregoing embodi- ment, sidewalls of the baffle body abut a majority of sur- [0003] An airfoil according to an example of the present 20 faces of the cavity. disclosure includes an airfoil body defining a cavity, and [0016] In a further embodiment of any of the foregoing a baffle including a baffle body including sidewalls and embodiments, the baffle body includes an inlet region defining an internal passage for conveying coolant. The and an exit region. The inlet region is configured to re- baffle body is situated in the cavity such that a majority ceive coolant, and the sidewalls are spaced apart at the of external surfaces of the sidewalls abut the cavity. 25 exit region to define one or more exit ports configured to [0004] In an embodiment of the foregoing embodi- eject coolant adjacent to an external surface of the airfoil ment, the sidewalls define an intermediate region be- body. tween an inlet region and an exit region. The inlet region [0017] In a further embodiment of any of the foregoing is configured to receive coolant, and the sidewalls are embodiments, the sidewalls taper from the inlet region spaced apart at the exit region to define one or more exit 30 towards the exit region. ports configured to eject coolant outwardly of the cavity. [0018] In a further embodiment of any of the foregoing [0005] In a further embodiment of any of the foregoing embodiments, the baffle body defines one or more exit embodiments, the inlet region tapers towards the inter- ports configured to eject coolant outward of the cavity. mediate region. [0019] In a further embodiment of any of the foregoing [0006] In a further embodiment of any of the foregoing 35 embodiments, the airfoil body is made of a first material, embodiments, the airfoil body extends in a chordwise and the baffle body is made of a second, different material direction between a leading edge and a trailing edge, and having a lesser thermal resistance than the first material. at least some of the exit ports are situated adjacent to [0020] A method of repairing an airfoil according to an the trailing edge. example of the present disclosure includes providing an [0007] In a further embodiment of any of the foregoing 40 airfoil body. The airfoil body has external walls extending embodiments, the exit region of the baffle body extends between a leading edge and a trailing edge providing a in the chordwise direction outwardly of the trailing edge. baffle. The baffle includes a baffle body defining an in- [0008] In a further embodiment of any of the foregoing ternal passage. Sidewalls of the baffle body define a first embodiments, the cavity is bounded by external walls of contour defining a cavity. The cavity extends inwardly the airfoil body. 45 from the external walls to define a second contour com- [0009] In a further embodiment of any of the foregoing plementary to the first contour. The method includes in- embodiments, the sidewalls of the baffle body have a serting the baffle into the cavity. complementary geometry to the surfaces of the cavity. [0021] In an embodiment of the foregoing embodi- [0010] In a further embodiment of any of the foregoing ment, the step of defining the cavity includes removing embodiments, the baffle body includes a plurality of cool- 50 material from the trailing edge to define an opening to ing features within the internal passage. the cavity, and the sidewalls of the baffle body are spaced [0011] In a further embodiment of any of the foregoing apart by an exit wall to define one or more exit ports embodiments, at least some of the plurality of cooling situated adjacent to the opening. features extend between opposed surfaces of the inter- [0022] In a further embodiment of any of the foregoing nal passage. 55 embodiments, the airfoil body is made of a first material, [0012] In a further embodiment of any of the foregoing and the baffle body is made of a second, different mate- embodiments, the airfoil body is made of a first material, rial. and the baffle body is made of a second, different mate- [0023] Although the different examples have the spe- 2 3 EP 3 170 981 A1 4 cific components shown in the illustrations, embodiments [0028] The engine 20 generally includes a low speed of this disclosure are not limited to those particular com- spool 30 and a high speed spool 32 mounted for rotation binations. It is possible to use some of the components about an engine central longitudinal axis A relative to an or features from one of the examples in combination with engine static structure 36 via several bearing systems features or components from another one of the exam- 5 38. It should be understood that various bearing systems ples. 38 at various locations may alternatively or additionally [0024] The various features and advantages of this in- be provided, and the location of bearing systems 38 may vention will become apparent to those skilled in the art be varied as appropriate to the application. from the following detailed description of an embodiment. [0029] The low speed spool 30 generally includes an The drawings that accompany the detailed description 10 inner shaft 40 that interconnects a fan 42, a first (or low) can be briefly described as follows. pressure compressor 44 and a second (or low) pressure turbine 46. The inner shaft 40 is connected to the fan 42 BRIEF DESCRIPTION OF THE DRAWINGS through a speed change mechanism, which in exemplary gas turbine engine 20 is illustrated as a geared architec- [0025] 15 ture 48, to drive the fan 42 at a lower speed than the low speed spool 30. Figure 1 schematically shows a gas turbine engine. [0030] The high speed spool 32 includes an outer shaft Figure 2 schematically shows an airfoil arrangement 50 that interconnects a second (or high) pressure com- for a turbine section. pressor 52 and a first (or high) pressure turbine 54. A Figure 3A illustrates a perspective view of an airfoil 20 combustor 56 is arranged between the high pressure and a baffle. compressor 52 and the high pressure turbine 54. A mid- Figure 3B illustrates a cross-sectional view of the turbine frame 57 of the engine static structure 36 is ar- airfoil of Figure 3A taken along line 3B-3B. ranged generally between the high pressure turbine 54 Figure 3C illustrates an isolated perspective view of and the low pressure turbine 46. The mid-turbine frame the baffle of Figure 3A.
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