SA515360813B1 - Ambient air cooling arrangement having a pre-swirler for gas turbine engine blade cooling - Google Patents

Abstract

A gas turbine engine including: an ambient-air cooling circuit (10) having a cooling channel (26) disposed in a turbine blade (22) and in fluid communication with a source (12) of ambient air: and an pre-swirler (18), the pre-swirler having: an inner shroud (38); an outer shroud (56); and a plurality of guide vanes (42), each spanning from the inner shroud to the outer shroud. Circumferentially adjacent guide vanes (46, 48) define respective nozzles (44) there between. Forces created by a rotation of the turbine blade motivate ambient air through the cooling circuit. The pre-swirler is configured to impart swirl to ambient air drawn through the nozzles and to direct the swirled ambient air toward a base of the turbine blade. The end walls (50, 54) of the pre-swirler may be contoured.

Description

— \ — ambient air cooling device containing a pre-swirl unit for cooling a gas turbine engine blade AMBIENT AIR COOLING ARRANGEMENT HAVING A PRE-SWIRLER FOR GAS TURBINE ENGINE BLADE COOLING FULL DESCRIPTION BACKGROUND THIS APPLICATION IS A PARTIAL COMPLETION OF US APPLICATION 857148 /17; Filed April 11 Y 0 1 1 (US Patent Attorney's Portfolio) Y 1 1 4 Ag Y 0 1 0 which is then incorporated herein by reference. The development then performed on this invention was then supported in part by Mall No. DE-FC26-© 0500142644 granted by the US Department of Energy.The US government therefore has no rights in this invention.The invention relates to the cooling of ambient air excited by the turbine blades of a gas turbine engine engine 985. Limitation The invention relates to a pre—swirler having a reduced pressure drop in this system. Optimally cooled through cooling channels through which 13a compressed air circulates. The amount of compressed air available for burning 0 | 00006051100._and this must be after him; Reduces engine efficiency 609170©6._therefore; Reducing the amount of refrigerant air drawn from the compressor for refrigeration is an important technique in the design of the modern Og Gasi. General description of the invention Tv

a in some gas turbine engine models; After the blades extend far in the radial direction, the Laws direction can include the blades; HAT Sle An array of ciphers. ideally; Cooling channels direct the cooling air from the base of the blade towards the dip edge where it is consumed in the flow of combustion gases by means of the cooling channel © that extends inside the blade axially in outward direction; Rotation of the blade, rotation of 6 m. The cooling channel is positioned lead, and a centrifugal force is exerted on the cooling air, which pushes the cooling air in the cooling channel axially to the outside. Cooling air exits from the blade and this creates a flow of cooling air inside the lash channel and this flow inside the cooling channel is a sucker that draws more cooling air from the rotor cavity around the base of the blade 0 into the cooling channel. Joo JAIL is the opposite of conventional refrigeration in which compressed air is directed through cooling ducts; Uncompressed air can be used; Jin the ambient air outside the gas turbine engine”; To cool the following blades. The static pressure of the ambient air is effectively greater than the static pressure of the rotary cavity to produce a cooling cooling fluid flow from an ambient air source in the direction of the cavity thus Ll Vo; The static pressure of the ambient air can be ashy by compressing the ambient air supply process in the direction of the rotary cavity, where the suction generated by rotating the blades pulls the ambient air from the rotary cavity through the cooling channels in the turbine blades, and thus a cooling circuit (Jl) was created. cooling circuit with ambient air. The suction force 50101101 helps draw ambient air into the rotary cavity. this way; Ambient air flow 0 can be maintained throughout the cooling circuit. however; While the static pressure of the ambient air and the centrifugal force of the generator are sufficient to generate flow in the capil duct, there is a small margin between the pressure difference that actually exists to operate the fluid and the minimum static pressure difference needed to make the coolant flow. as a result; Attention has been paid to the cooling circuit design for maximum air transfer efficiency. TV

— ¢ — Brief Explanation of Drawings The invention is explained in the following description in light of the figures shown: Figure 1 is a schematic cross-sectional gladd of a side view of a part of an induced air refrigeration circuit. Figure ¥ is a schematic perspective view For a pre-circulation vortex unit of an excited air cooling circuit in accordance with Fig

3 figure? It is a view of the entrance [1716] of the pre-spin unit according to Figure YO Figure 4 Ble from a sectional view of the pre-spin unit according to Figure oF showing the portion part of the guide vanes and the inner shroud.

Yo Figure o is a cross-sectional view of the pre-spin unit according to Figure 1 ¢ showing part of the steering blades and the outer shield. Figure T is an upper view showing the topography of the pre-spin_unit according to Figure 8 Figure 1 is a view showing the topography of the tribal spin unit according to Figure #.

Vo Figure A is an illustration of a flowline refrigerant streamline in a pre-whirl unit without the properties disclosed here. Figure 9 is an illustration of a refrigerant flow line in a pre-spin unit containing the properties disclosed here. Detailed description:

Ye Inventors invented a pre-cooled vortex unit device cooled by excited ambient air to cool the turbine blades of a gas turbine engine; Whereas the pre-spin unit includes peripheral end walls

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Contoured end walls to improve the flow properties indicated by uniform coolant flow through the pre-spin_unit. The pre-swirl unit swirls an ambient airflow prior to introducing the flow to the rotating turbine blades thus effectively piggybacking the coolant flow to the inlets of the blades' cooling ducts. Surrounding terminal © walls reduce flow pressure losses; Thus the flow efficiency through the slewing unit is increased

tribal which; in turn; And increase the efficiency of the gas turbine engine. Figure 1 shows a schematic cross-section of a side view of part of an exemplary ambient air refrigeration circuit 01 comprising: source 11 of ambient air; At least one VE passage jee providing fluid communication between the daly VY source and the yo pre-swirler unit V7 pre—swirler plenum optionally housed in a VY strut supporting the vortex unit Tribal 70; rotary bore 01 adjacent to the ¢YY turbine blades and the cooling duct inlet (other than Ome) FT cooling duct and YS cooling duct outlet in each of the YY turbine blades which can be or It is not located at the edge of the turbine blade 77. .._ Once in the air supply passage € 1 the ambient air is converted into coolant 74. The coolant 1 YA travels through the jee Air supply VE where the blower enters the pre-swirl unit OT which is an annular shaped plenum blower device that supplies the cooling fluid YA to the pre-swirl_unit VA In the pre-swirl_unit VA a fluid is swirled Cooling YA around the longitudinal axis Yo longitudinal axis of the Jay YY rotor disc The coolant YA to the inlets of the cooling channel, for example, either directly from the circulation unit or Before 08 or after the refrigerant YA travels through the gap between the rotor 1? and the base of the turbine blade VY and then the refrigerant YA travels through each cooling channel .77 in channels Cooling (FT) When the turbine blades rotate VY around the longitudinal axis 0 of the rotary disc FY (known as the axis of rotation) a centrifugal force is in an axial outward direction "? Ally the refrigerant YA excites through the cooling channels YT The refrigerant YA is expelled from the outlet of the Yo cooling channel 79 and into a hot gas path 4 ? Where hot gases flow

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-- LY gases movement of the YA coolant through the cooling channels YU and out of the outlet of the YA cooling channel creates a suction force that draws the YA coolant from the rotary cavity 010 into the cooling channel 77 to replace the coolant YA output. The static pressure of the ambient air forces the YA refrigerant towards the rotary cavity 0700 to replace the YA refrigerant which is drawn into the YT refrigerant channels Jal, © completing the ambient air refrigeration circuit .01 Fig. 01 She Y on a schematic perspective view sang) Pre-swirl VA of an ambient air cooling circuit 0 from the rear end of a gas turbine engine; With the outer shield removed. A illustration of an inner shield TA containing a fixed diameter 0© and a set of 7 guide vanes; placed in an annular array around the longitudinal axis of the turntable, 71. The pre-spin unit YA receives an axially flowing, annular YA coolant flow of YA coolant delivered by a blower Sas VT imparts a circumferential motion resulting from a vortex around the longitudinal axis 0 of the turntable ©1. As shown in Figure oF showing the inlet side of an exemplary model of a pre-cycled VA unit. EY guide vanes specify a set of nozzles ;; YA coolant routing each nozzle 8a0022 ;; formed between and set 0 by guide vane first 47; peripherally adjacent guide vane 8 ;; outer end wall 00 of inner shield FA and inner end wall 94 of outer shield 1 which rotate the LEY guide vanes each nozzle 44 thus defines part of the cooling circuit .01 unlike conventional nozzles; The exposed end walls do not have a fixed diameter fe instead; End walls are enclosed in both circumferential direction 00 circumferential direction and cE direction and can undulate around the fixed diameter 17 axial direction 00 associated with the steering vanes known as vortex aerodynamic loss aerodynamic loss of steering edge VY can develop at the junction lly Ve horseshoe vortex horseshoe inside the orifice 44 there is an 800 wall of the guide vane 47 and an end wall Ve leading edge to form in relatively less fluid flow areas where there is pressure Jas vortices The coolant vortices close to the end walls and the pressure side is slowed aw Static above Yo

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—y— V1 pressure side and/or VA suction side relative to other areas within the YA refrigerant is determined by several aerodynamic factors including the friction associated with these surfaces. As a result; Refrigerant 74 approaches in a region A close to the VY junctions which can move relatively slowly compared to the central AY regions © within Crater 44;. Furthermore it; The YA refrigerant encountering the VE guide dls of the £Y guide vane causes an old bow wave dase at the VE guide edge where static pressure is formed compared to the static pressure within other flow zones in the flow. Subsequently; The moving fluid exits relatively slowly and static pressure from the region 80 close to the VY intersections compared to the central regions AY inside the nozzle ;;. Where the force of the vortex on horseshoe-shaped 0 is related to the amount of velocity graduated between the two regions and the magnitude of the static pressure graduated between the two regions. Relatively strong 11 horseshoe vortices can be formed in the £6 nozzle of the exposed type about it here. The losses associated with enlarged horseshoe vortices are magnified Laie The guide vanes have a low aspect ratio. A shorter radial height and a longer airfoil length give horseshoe vortex 1 a greater chance of moving closer to the central region 87. Hence; The benefit of including circumferential end walls (50;(OF) in an ideal model of a pre-swivel unit .47 that has a low side rate of the VA guide vanes relatively faster than the flow of the moving region in the YA moving region) is also mentioned. Furthermore, coolant towards the moving region 71 of the horseshoe vortex Af leg Jay will tend to draw as the swirler in the orifice to the device forming the Lae Af vortex relatively faster with flow Leg 0 The leg 84 can be pulled out of the AY The relatively faster moving area is the central regions in an outward diagonal direction 77. The pull of the AT The radial internal vortex in the shape of a horseshoe inside the crater has a greater amount of loss Dynamic antenna AY man 84 to central area

VY will still be in Zone 80 close to the Af intersections in the stream rather than what would happen if the Man Tv

—A— less; Thus the aerodynamic loss in the area is a flow rate where the flow rate is problematic. And/or pressure is a velocity gradient without being tied to a particular theory; It is believed that the gradual reduction in speed is 51060915._therefore; The end walls here of vortex will reduce vortex force effective in reducing gradient velocity and/or static pressure; which reduces the vortex force on © to the vortex on Af moreover; End wall design helps man Ve horseshoe shape so VY stays closer to zone 80 near intersections 170 horseshoe shape Circumference includes LEE inside nozzle AY Reduce aerodynamic loss inside The central area on each raised area is also seen as a raised area 001 hump exposed contouring 001 protruding the LEY camber of the VT guide vane end wall adjacent to the pressure side 0 Here is an area The end wall is more inside a crater when compared to an end wall without a hump on a recessed area or hollow area 011 valley The perimeter also includes a groove. Here is an area where the exposed dle 011 groove LEY each end wall between the guide vanes any NY end wall recessed from a mouth at the concourse into a groove end wall can be regarded as a region of diameter Fixed. each 0171 or groove 001 end wall orifice region without camber VO a region where a constant Je resides; or it may only have a diagonal dimension defining the fixed diameter portion of the theoretical end wall; Where the end wall actually surrounds diagonally and axially to the outside of the theoretical dimension Occupying 017 or a groove 001 Each end wall can include humps AT Lies dimension

WS or each end wall can be delimited lla) only a small portion of the end wall 0 does not leave a fixed diameter actual area (eg neutral). Lay) oY and a groove 001 by humps close to Av intersections in region YA serve to cause the coolant 001 to think that the humps by reducing the cross-sectional area 001 are flowing faster than it would without the presence of the VY humps of the nozzle; ; In area 80 near intersections 77. with cross sectional area rapidly. It is also believed that the grooves YA have less surface area where the YO coolant must flow

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011 valleys works in order to have the coolant YA in the central region AY inside the nozzle £4 so that it is slowed down by the increased cross-sectional area of the nozzle ?4. An increase in coolant velocity YA in the region Av close to the VY junctions and a decrease in velocity of the coolant YA in the central region AY results within the nozzle; ; for a lower incremental speed which; In turn produced by a weaker vortex on horseshoe-shaped © Noe without humps or humps Static pressure in the region Ae close to the VY intersections is relatively high due to the slow velocity of the coolant WTA by increasing the velocity in the region Av near the VY junctions static pressure is reduced. without groove 007 static pressure in the central region AY inside the nozzle ;; Relatively low due to the high velocity of the 0 refrigerant 78. By reducing the velocity in the central region AY inside the nozzle o£ the static pressure is increased. Reducing the relatively high static pressure in region 80 close to the VY junctions and increasing the relatively low static pressure in the central region AY inside the nozzle £4 results from a gradual pressure Jai which; in turn” results from a weaker horseshoe vortex No as well as eld because the coolant in the central region AY inside the nozzle £4 has been slowed down; 10 there was less tendency for the leg 84 of the inner diagonally horseshoe vortex AT to be pulled in an outward diagonal direction 37. As the horseshoe vortex 760 passes through the groove of the end wall and is reflected off the horseshoe vortex 71 in such a way relative It is believed that it contributes to the failure to draw the horseshoe vortex 71 km into the central region AY inside the crater;. In another way the adhesion of the horseshoe vortex 710 to the terminal wall is better mentioned. _By better adherence to the terminal wall; The propagation of aerodynamic losses associated with the horseshoe vortex 710 within the Jala AY crater's central region is attenuated. This reduces overall aerodynamic loss; Which increases engine efficiency. the shape ; It is a sectional view of the pre-swirl saad VA according to Figure oF showing a diagonal inner part of the guide vanes 47 and the inner shield FA with the removal of an outer part diagonally of the guide vanes 47 and the outer Yo shield 06. An inner part is shown diagonally For a set of eff craters each of which specifies a wiis ng

“yam £1 of first guide vane VT pressure side FA of the inner shield 00 via the outer end wall coolant enters 4 to the inlet end LEA of the circumferentially adjacent guide vane YA and suction side

Vo for the nozzle ;; While traveling primarily in an axial direction relative to the longitudinal axis 0 it travels in a transition direction that has a component in 111 and exits from the output end oF) of the turntable 610 in the axial direction and a component in the circumferential direction 0 in the model ideal; The inner shield 78 and/or the outer shield 07 can be a vane assemblies. Monolithic body dep assemblies are traditionally made from turbines components in turbines Qartala able aa This configuration is necessary wring of vanes which are assembled into vane ring subcomponents involving high cost lly vane rings due to factors associated with larger size of vane rings 0 and turbine disassembly and assembly thermal growth to manufacture a single body of this size and growth problems Thermal these vane rings assembled often the vane ring itself which often requires dismantling the vane ring can be sle [01015] includes couplings between sub-components that change with operation. in the orifice between adjacent sub-components; Or it could be a circumferential gap. There is a different aerodynamics circumferential gap. And that alone; Provides aerodynamics 1 col The Sle component can extend diagonally aligned. The joint may or may not be diagonally further apart. Subsequently; When subcomponent gases travel when the nozzle has a circumferential component Jie opposite a gap between adjacent subcomponents” dag during the gases can experience a step. It can be a step to the “circumferential component” above or below; depending on whether the first subcomponent extends diagonally out of the adjacent subcomponent 0; Or do not extend diagonally far. All kinds of steps are whirlpools in the flow; These vortices are the same type of aerodynamic loss until the vortices are formed in the shape of a horseshoe and outer shield 576 no YA due to the smaller size and lower temperatures; The inner shield .0 suffers from the above limitations and can therefore be manufactured as a one-piece component. Allows a single-module structure

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-11- Between assembled sub-components, joints of nozzles to avoid aerodynamic losses associated with joints. 4 4 This leads to; In turn, a lower pressure loss resulting from the transmission through the nozzle shows an outer part oF according to Fig. 18. The pre-swirl saa Fig. © is a sectional view, the shield EY diagonally of the guide vanes 47 and the outer shield 6 ©; With the removal of an internal part diagonally for the steering blades

Wis each determines eff An outer part is radially positioned for a group of nozzles FA inner £1 1st guide vane VT by inner end wall 54 of outer shield 0 pressure side

EA Guide vane circumferentially adjacent VA and suction side of vortex unit VA from top view showing topography of an exemplar of inner shield Ble 6 Fig. 6 adjacent to pressure side 001 in exemplar shown; Shown Tribal VA cams Can be positioned close to 1/3 of the way below the 001 line Ady £1 cams of first guide vane L 1 00 trailing of first vane to edge VE diameter from guide edge 117 chord line ji

Te visible in a circumferential direction 011 in the ideal model shown; The groove is 1.7. spiral edge EA approximately to half of the end between the first guide vane 47 and the vane adjacent peripherally to the first vane 47. In VE it is shown that it originates from the guide vane 71 in the shape of a horseshoe Road horse below the AB line of the roughly placed groove there is 101 exemplary pattern shown at the lowest point 1 YT of the first guide vane to the edge diameter VE of the guide edge 1177 can also be set 84 leg To move over the ada so that 71 is placed after the leg 84 of the horseshoe-shaped spiral

AY groove (TOE (as shown in from a view showing the topography of an exemplary model of the outer shield 0 of the pre-swirl_unit Ble 1 Fig. 1 placed on the center located mirror diagonally inward at mirror lal) according to Therefore, it is #1 and the longest outer clad 01 is located diagonally in the direction of the gall under the outer shield 257. Where, by excluding this length EY, there is thus more space between adjacent guide vanes, which appears Smaller but the 011 and the grooves of the 001 additional 1 cam to match the size according to the figure shown are perfect. Affects any circumference 011 and the grooves 001 could not be virtually smaller. Camber Produces the aerodynamic effect affecting the detection perspective. contour Yo ng

-?1- Figure A is a refrigerant stream routing AYA pre-swirl unit without the properties disclosed here using fluid modeling The flow line 114 legs Af represents a horseshoe vortex WY It can be seen that when the guiding edge VE of the first guide vane, Tag £1, encounters the leg of AE in detachment from the pressure side of the first guide vane, LET, while reversing the oo nozzle £4, the flow stream is transmitted; 11 in the direction of the suction side VA of the circumferentially adjacent guide vane 478 in the direction of the diameter edge 176 of the circumferentially adjacent guide vane LEA when doing so; The outflow stream 1 4 may also move upwards out of the plane of paper in the direction of the central region AY inside the nozzle; of and cause aerodynamic loss. Figure 9 is an illustration of the YA coolant flow current in a VA pre-swirl unit having the 0 properties disclosed here using fluid modeling. When the guide edge VE encounters the first guide vane (£7) the inrush current separates; YY of the leg Af of the horseshoe vortex Vi slightly from the pressure side YT on the reverse of the figure VA is transmitted GIVE the direction of the suction side VA of the circumferentially adjacent guide vane $A as it travels inside the nozzle; © in the direction of the diameter edge 176 of the circumferentially adjacent vane LEA instead; adhere to the flow stream 174 1 Beside the pressure VT of the first guide vane £1 for a longer distance. Moreover, the inrush current is less likely to separate from the plane of the paper to the same degree. As a result, in a pre-spin unit disclosed here, the leg 84 of the vortex is generated in the form of Horseshoe 710 Less aerodynamic losses resulting in more efficient gas turbine operation ad From the above, it is clear that the inventors have realized a new way to develop aerodynamics | The inventors also made further developments on the pre-spin sans to improve aerodynamics further. Inside say tribal swirl. Subsequently; The above represents an improvement in the field. Whilst various embodiments of the present invention have been illustrated and described (la Yo it will be evident that these embodiments are given as an example only. Several changes can be implemented in

— \ _ and substitutions without departing from the invention. Subsequently; The invention is intended to be limited only by the content and scope of the subsequent claims. TV

Claims (1)

-T1- Protection Elements (Sas) Gas turbine engine 985; It includes: an air cooling circuit 8751671-21 lass that includes a cooling channel placed in a turbine blade and connected via the fluid to an ambient air source providing a cooling fluid: and © cpre—swirler ald unit includes: an inner shroud a stouter shroud a set of cguide vanes each rotating from the inner shroud to the outer shroud shroud 0 where the guide vanes adjacent peripherally guide vanes specify nozzles Nozzles corresponding to Lad between the nozzles nozzles specify the portion part of the “cooling circuit” each nozzle iss defined by a pressure side pressure side of a first guide vane; Suction side 6 5101000 of adjacent guide vane » Jas outer end wall defined by the couter shroud and inner end wall defined 1 by the inner shroud ¢ Where the forces applied to rotate the turbine blade excite the cooling fluid 0 through the cooling circuit and where the pre-swirler unit is configured to impart a swirl to the cooling fluid fluid drawn through nozzles 0022165 and to direct the swirled cooling fluid 0 in the direction of the base of the turbine blade The gas turbine engine according to the dua protection element. The inner shroud is formed as a monolithic body. *.The gas turbine engine 985 according to Clause 1, where the outer shroud Yo was formed as a monolithic body zal ran out -M1- The gas turbine engine 985 according to the Sua protection element has an inner end wall and an outer end wall, each of which includes a valley groove placed between adjacent guide vanes. lo} D. The gas turbine engine according to the protection element ;; Where the valley is placed after a vortex formed in the drawn cooling fluid by the leading edge of the first guide vane during the rotation of the turbine blades 001 end wall Sua) According to the protection element 985 gas turbine engine Karhla 1, each of which includes outer end wall and inner end wall. guide vane pressure side adjacent For the pressure side, the hump Veo “. The gas turbine engine according to claim 1 where the Ad hump is placed at approximately one-third of the length of the chord line jig of the first guide vane of the dla Leading edge of the first guide vane. clash A gas turbine Wy gas turbine engine for protection element sil cooling cooling circuit Y also includes an air supply passage prepared for supplying cooling fluid ambient air source to ‎aul san tribal ‎pre— ‎swirler 4. The gas turbine engine 985 according to protection element (A) also includes a prop 5 [5100] supporting the pre-swirler unit in which the air supply bypass is placed .passage Tv -?1- 0. gas turbine engine 985; It includes: an air cooling circuit 8751671-21 lass comprising a cooling channel placed in a turbine blade and connected via the fluid to an ambient air© supply providing a fluid coolant 109a000; Where the forces applied to rotate the turbine blade excite the cooling fluid through the cooling circuit 101 The development includes: A pre-swirling unit cpre—swirler Including an inner shroud Configured as an entity ¢emonolithic outer shroud configured as a ¢monolithic entity 0 and a set of guide vanes placed in an annular array between them defining the pre—swirler unit A set of nozzles determines the ja of the cooling circuit. Each nozzle includes: an outer end wall defined by an outer shroud between guide vanes. contiguous; inner end wall defined by the inner shroud Vo between adjacent guide vanes; pressure side and suction side of adjacent guide vanes; Where the Boag pre-swirler is conditioned to impart a circumferential motion 00 about the longitudinal axis of a 0156 rotor to a wil cooling fluid drawn through the Nozzles and to direct a fluid swirled cooling Y. I'm cooling towards the base of the turbine blade 1. The gas turbine engine according to claim 10, wherein the inner end wall and outer end wall of each dag nozzle include a corresponding valley groove. Yo Tv -11- 1. The gas turbine engine according to Clause 01 where the dag of each outer end wall and the inner end wall of the inner end wall nozzle includes corresponding humps adjacent to the pressure side Pressure side of a corresponding guide vane. lo} 0. The gas turbine engine according to claim 10; the cooling circuit also includes an air supply passage prepared for the supply of pre- aul san fluid to ambient air Ambient air source cooling fluid cooling cswirler where the air supply passage is placed inside a strut supporting 0 pre-swirler unit 04 . gas turbine engine turbine engine 985; Includes: Cooling channel 8751671-21 lass air cooling circuit A cooling circuit housed in a turbine blade and connected via the fluid to an ambient air Vo supplying coolant cooling fluid and sas pre-swirl cpre—swirler includes: ¢ inner shroud stouter shroud outer shield A set of guide vanes positioned between the inner shroud and shield 0 outer touter shroud where inner shield dinner shroud outer shroud and guide vanes group guide vanes specify array als 81i8007 for 70022165 nozzles specify part of the ambient air cooling circuit cambient-air Each Nozzle is attached to two adjacent guide vanes”; wall 600 100617 for outer shroud © and outer end wall for inner shroud ¢ inner shroud Tv m \ — where the Nozzles are fitted to direct the cooling fluid passed through them in the direction of a set of cooling fluid inlets located at the bases of the adjacently positioned rotating blades; And where the nozzles impart a circumferential motion to the cooling fluid © flowing through them around the axis of rotation around which the rotating blades rotate. The gas turbine engine according to the protection element (VE) wherein the inner shroud and the outer shroud are each composed as monolithic bodies 0 corresponding. The gas turbine engine according to the VE protection element, where the inner end wall of the outer shroud and the outer end wall of the valley include a nozzle groove for each nozzle, the inner shroud of the shield Interior outer end wall Views. Vo 11. The gas turbine engine according to the VE protection element, where the inner end wall of the outer shroud and the outer end wall of the hump include a nozzle for each inner shroud For the inner shield, the outer end wall corresponds to the guide vane. For the pressure side, the guide vane corresponds to the pressure side > 0 80. Gas turbine engine according to protection element VE cooling circuit also includes jee (Led) air supply passage for ambient air supply air 80701601 from ambient air source ambient air to the pre-spin_unit cpre—swirler | 8 Where the Jala air supply passage is placed, a strut supports the pre-swirler .pre—swirler Tv unit. Hayy fs & ES: Yasis: 4:* 3: 5 1)2 = 8 a b >3 3 + gl: 1 p 1 - b a 1 Riis tenia Fy ; 1: : Ab 1 a Allite : { ais 3 ie : ) EB a but 1 Eo a x 5 STOLL 5 5 ; . 8 SA y . 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B , 2 !SESS RS ER CRE A HAY TTT TTY jt SURE L TEK BERR EAE SE oi 2 Sr EE LT ROT sek i Ss BER SO D TAH fF LAH EL AUM EM AL LAK PAE ‏ IEEE Te ed on JON “eT IEEE Te ed PI Ci an es et Ce ae st aa” 1: 0 RI 2 a 8 Agenda and BDA 2 x: CH oo Tal 1 a re a eT RT a la la { a a t 1 y a Pt BY a a a oo EEE wi a a 1 0 of a Wee Om TRL k A L as } 2 8 RN fears SNH ees p So 8 8 Hay EE S IS District 0 and B A I A 1 3 AA EL RE AD SEER Rah ey AR * Mi He SE A 3 A SY L seb ily 3 = | 0 D ar dik LO rane EN RT Jed ho his mother A Taya A SEL A 8 9 Fin EE WEE PRR ER San 3 A FER SRR l i Le a TRA 2 M Rg A 'L : rs ERE ER L A L A S 0 Hay L AR SE 2 Da a= Fa SRILA wed A 2075 we = FER A A A a fie RIE BAL ok: SEER Does -~ RENE SEE Slow Etc ¥ ERNE > TD 1 Ce a a a a a a zo b 8 a rf uh a = { en @ oo = pes ran out until you make | l a r ged a : a from m a l a a oo : 3 3 ." m src ra = Cf 4 A "8 cm b | ; : m / a' 0 4 3 b | pp # / %/ 5 1 y / | «< / a - x 3 ; / A z ˚ a ma daq / / / 1 bin ar ara a i ba a | Tg A \ M Tava The _ ]= pes yay L 1 and F A - - : f m = i 0 Sl - pd Mi A / Id Lo SR |> | / \ oF a food / / / 0 ! w 1 # 1 / | / AY 0 > 0 / 1 0# Reef Ie Teva The validity period of this patent is twenty years from the date of filing the application, provided that the annual financial fee is paid for the patent and that it is not invalid or forfeited for violating any of the provisions of the patent system, layout designs of integrated circuits, plant varieties, and industrial designs, or its executive regulations issued by King Abdulaziz City for Science and Technology; Saudi Patent Office P.O. Box TAT Riyadh 57??11 ¢ Kingdom of Saudi Arabia Email: Patents @kacst.edu.sa