Two stage rotor assembly with improved coolant flow
5 claims: 1 independent, 4 dependent
- 1ΑΞΙΩΣΕΙΣ 1. Συγκρότημα ρότορος (στροφέως) περιλαμβάνον πρώτον καί δεύτερον συναξονικούς καί συμπεριστρεφοαένους ρότορας μηχανής άεριοστροβίλου, έκαστος τών όποιων περιλαμβάνει ένα δίσκον έχοντα μίαν προσθίαν οψιν, μίαν δπισθίαν δψιν, μίαν ένεργόν στεφάνην καί πολλά ώτία άπέχοντα περίφερείακως καί εκτεινόμενα άκτινικώς πρός τά έξω τής στεφάνης, καί μίαν σχισμήν βάσεως πτερυγίου καθοριζομένην μεταξύ γειτονικών περιφερειακώς ώτίων,ένθα αΐ σχισμαί αυται έκτείνονται άξονικώς έκ τής προσθίας πρός τήν όπισθίαν δψιν, μέσα σχετικά μέ τήν προσθίαν δψιν τού πρώτου ρότορος ατινα καθορίζουν έν πρόσθιον διαμέρισμα παραλαβής μιας -17παροχής ψυκτικού άέρος, μέσα διατηρήσεως άποστάσεως, έκτεινόμενα μεταξύ τής οπίσθιας οψεως τού δίσκου πρώτου ρότορος καί τής προσθίας οψεως τού δίσκου δευτέρου ρότορος καί έφαπτόμενα μέ τούτους ώστε νά περιστρέφωνται μετά τούτων, ένθα τά μέσα άποστάσεως καί ot δίσκοι ρότορος καθορίζουν έν ένδιάμεσον δακτυλιοειδές διαμέρισμα ψυκτικού άέρος κείμενον άκτινικώς πρός τά έσω τών μέσων άποστάσεως καί έκτεινόμενον άξονικώς μεταξύ τών πρόσθιας καί οπίσθιας όψεων δίσκου, καί ένθα έκαστος ρότορας περιλαμβάνει πολλά πτερύγια ρότορος, έκαστον δέ πτερύγιον έχει μίαν βάσιν, μέ μίαν βάσιν διευθετημένην είς έκάστην σχισμήν καί καθορίζουσαν μέ τήν σχετικήν της σχισμήν μίαν άξονικήν δίοδον ψυκτικού άέρος μέσω τής σχισμής, έκ τής πρόσθιας πρός τήν δπισθίαν οψιν τού άντιστοίχου δίσκου, ένθα τό πρόσθιον διαμέρισμα, at δίοδοι μέσω τών σχισμών δίσκου πρώτου ρότορος, τό ένδιάμεσον διαμέρισμα ψυκτικού άέρος καί at δίοδοι μέσω τών σχνσμών δίσκου δευτέρου ρότορος εύρίσκονται είς σχέσιν έν σειρά ροής ρευστού, δπότε ψυκτικός άήρ ρέει έκ τού προσθίου διαμερίσματος είς τάς σχισμάς δίσκου πρώτου ρότορος καί μέσω τούτων, έκ τών σχισμών δίσκου πρώτου ρότορος είς τό ένδιάμεσον διαμέρισμα ψυκτικού άέρος, καί έκ τού ενδιαμέσου τούτου διαμερίσματος ψυκτικού άέρος είς τάς σχισμάς δίσκου δευτέρου ρότορος καί μέσω τούτων.
- 2Τό συγκρότημα ρότορος σύμφώνως πρός άξίωσιν 1, ένθα τά μέσα διατηρήσεως άποστάσεως έφάπτονται μέ τήν όπισθίαν οψιν δίσκου τού πρώτου ρότορος περίπου κατά ενα συνεχή κύκλον συναξονικόν πρός τόν άξονα τού ρότορος καί κείμενον άκτινικώς -18πρός τά έσω τών διόδων ψυκτικού άέρος, διά μέσου τών σχισμών τοΰ πρώτου δίσκου, καί τά μέσα δίατηρήσεως άποστάσεως έφάπτονται μέ τήν προσθίαν δψιν τοΰ δίσκου δευτέρου ρότορος κατά μήκος ένός κύκλου συναξονικοΰ μέ τόν άξονα τοΰ ρότορος καί κειμένου άκτινικώς πρός τά έσω τών διόδων ψυκτικού άέρος, διά μέσου τών σχισμών του δευτέρου δίσκου.
- 3Τό συγκρότημα ρότορος συμφώνως πρός αξίωσιν 1, ένθα τά μέσα δίατηρήσεως άποστάσεως περιλαμβάνουν ένα άξονικώς έκτεινόμενον δακτυλιοειδή φορέα σφραγίσεως (στεγανοποιήσεως) μαχαιρωτής άκμής έχοντα Ιν πρόσθιον ακρον καίεν οπίσθιον άκρον, ένθα τό πρόσθιον ακρον περιλαμβάνει μίαν άκτινικώς ρός τά έξω στρεφομένην καί περιφερειακώς έκτεινομένην επιφάνειαν, ή δέ όπισθία δψις τοΰ πρώτου δίσκου περιλαμβάνει μίαν άκτινικώς πρός τά έσω στρεφομένην καί περιφερειακώς έκτεινομένην επιφάνειαν, ήτις κειται άκτινικώς πρός τά έσω τών σχισμών πρώτου δίσκου καί εφάπτεται μέ τήν άκτινικώς πρός τά έξω στρεφομένην επιφάνειαν ήτις καθορίζει μεταζύ των μίαν πρώτην περίπου κυλινδρικήν ένδιάμεσον δψιν, ένθα τό ρηθέν όπίσθιον ακρον περιλαμβάνει μίαν άκτινικώς πρός τά έξω στρεφομένην καί περιφερειακώς έκτεινομέτ,ην επιφάνειαν, ή δέ πρόσθια δψις τοΰ βέυτέρου δίσκου περιλαμβάνει μίαν άκτινικώς πρός τά έσω στρεφομένην καί περιφερειακώς έκτεινομένην επιφάνειαν, ήτις κειται άκτινικώς πρός τά έσω τών σχισμών δευτέρου δίσκου καί έφάπτεται μέ τό οπίσθιον άκρον τής άκτινικώς πρός τά έξω στρεφομένης έπιφανείας, δπότε καθορίζεται μεταξύ των μία δεύτε ρα περίπου κυλινδρική ένδιάμεσος δψις.
- 4Το συγκρότημα ρότορος συμφώνως' πρός αξίωσιν 3, περιλααθάνον μέσα έπικαλυπτικής πλακός πρός τά κατάντι τοΰ -19πρώτου δίσκου καί έν έπαφή μέ τήν όπισθίαν οψιν τοΰ πρώτου δίσκου, όπότε καθορίζεται έν πρώτον οπίσθιον διαμέρισμα μεταξύ τοΰ ενδιαμέσου διαμερίσματος καί τών άξονικών διόδων ψυκτικού άέρος, μέσω τών σχισμών τοΰ πρώτου δίσκου,, ένθα τό ένδιάμεσον διαμέρισμα, τό πρώτον οπίσθιον διαμέρισμα καί αί. δίοδοι ψυκτικού άέρος μέσω τών σχισμών τοΰ πρώτου δίσκου εύρίσκονται ύπό σχέσιν ροής ρευστοΰ έν σειρά.
- 5Τό συγκρότημα ρότορος συμφώνως πρός άξίωσιν 4, ένθα δ πρφτος δίσκος καί τά μέσα διατηρήσεως άποστάσεως περιλαμβάνουν μέσα καθορίζοντα ανοίγματα είς τήν πρώτην ένδιάμεσον οψιν, πρός μέτρησιν τής ροής, ψυκτικού άέρος έκ τοΰ πρώτου οπισθίου διαμερίσματος πρός τό ένδιάμεσον διαμέρισμα, καί δ δεύτερος δίσκος καί τά μέσα διατηρήσεως άποστάσεως περιλαμβάνουν μέσα καθορίζοντα άνοίγματα είς τήν δευτέραν ένδιάμεσον οψιν, διά τήν ροήν ψυκτικού άέρος έκ τοΰ ενδιαμέσου διαμερίσματος πρός τάς διόδους ψυκτικού άέρος, διά μέσου τών σχισμών δίσκου τοΰ δευτέρου ρότορος.
Independent claims5
54 paragraphs in 2 sections, as filed
<img file="GR82527B_D0001.tif" />
DIVISION ROTOROS COMPLEX WITH 33LTIMES
FLOOR REFRIGERATOR
Technical Field * This invention relates to rotor (rotor) gas turbine engines, and more particularly to the cooling of the rotor disc and the blade base.
Old villa technology or
In the hot turbine section of a rotary blade f / d * 7 there is or is a need for blades, an active turbine disc rim and two-blade discs to cool during operation. This has typically been accomplished through the cooling air passage through the disc, through axial passages formed in the slit of the base of the blades between the inner end of the base of the blades and the active rim. * The coolant flow flows through the slot once downstream and discharges into a compartment downstream of the disc.
It is also common for air turbine engines (AIRFOILS) to be hollow, that is, to contain passages and / or compartments therefor to keep the airflow below a pre-set temperature. In the prior art, it is known to provide a measured amount of cooling air to the upstream portion of the disc inside the hollow spacers, through radially extending passages through the expanded disk rim portion. These passageways provide a measured flow of communication through radially extending channels through the bases of the hollow aerosol blades.
In a two-stage turbine, both steps are cooled by the use of a six-compartment coolant to the first-stage disc bracket. * The cooling air through the rim of the second-stage disc and the blades is directed from the upstream portion of this compartment, through axial holes in the first disk, into a narrow compartment formed between them. second installment. * C refrigerant air passes through 7 ° C
-3 intermediate compartment in the hollow aerial portion of the second-stage rotor, by means of metered flow diodes extending approximately radially through the enlarged rim portion of the disc. Measured flow channels are channeled through the bases of the vents of the hollow aerial feeders.
It is desirable or minimized the amount of coolant flow that is needed to maintain acceptable operating temperatures of the components, as this improves the engine's performance. It is also desirable or avoided to create holes through the discs, because these holes weaken the disc and limit its life.
Development of the invention
It is for the purpose of the present invention to be a two-stage turbine assembly with improved means for cooling the air in<sub>T.</sub>one and the blades of both turbine rotors.
According to the present invention, a two-stage turbine has a first-degree disc with many peripherals spaced between the base slits of the blades, the atoms thereby extending azoniously around their circumferential and peripheral regions. absent between the base slits of the wings, the spines extend axially therewith around its circumference, and within them the wings are arranged, There are means for maintaining distance between the two discs and engaging them, fixed in an intermediate compartment by cooling between them.
-4 radially inwardly positioning the slots in the flaps, where the trays and spacers are manufactured and arranged so as to cool one compartment airflow upstream of the first flap through the flaps. the back side of the first disc and radiated inwardly, within the said intermediate compartment between the discs, from where it runs within the slots at the base of the flaps of the second disc and through them to its rear side.
In a preferred embodiment, the aerosols are bellows and a measurable portion of the cooling air passing through the slots of the flaps of each tray is radially directed outwardly through the inner flats.
An important feature of the present invention is the removal of axial holes through the first disk, which were used in the prior art to bring cooling air downstream of the second disk.
Fig. 1 is a simplified sectional view of the turbine section of a gas turbine engine, incorporating the features of the present invention.
Fig. 2 is a sectional view generally performed along line 2-2 of Fig. 1. Fig. 3 is a sectional view generally performed along line 3-3 of Fig. 1.
,
-5Fig. 4 is a sectional view generally performed along line 4-4 of FIG. 1.
Fig. 5 is a perspective view, generally seen to the rear, of a section of the annular rear flap retainer for the first-stage turbine rotor.
Fig. 6 is a partially cut trench, generally performed along line 6-6 of Fig. 3.
Fig. 7 is a sectional view generally performed along line 7-7 of Fig. 6.
Optimal Design of the Turbine Section A turbine section is considered as an exemplary embodiment of the present invention, wherein the turbine section is generally represented by only reference number 10. first two steps. The first-stage rotor assembly is generally represented by reference number 12. The second-stage rotor assembly is generally represented by reference number 14.
The first rotor assembly 12 comprises a disc 16 with many blades 18 abutting around its periphery. <sup>n</sup>Each flap 18 comprises a base section 22 and an airfoil section 20 with a platform 25 bushes thereafter. Referring also to Fig. 2, we see that the base portion 22 has a base end 24 of a spruce shape arranged on a similar spruce shape 26 extending axially through the tray 16, from the front 23
-6 ° of 30. At slits 26 formed between the so-called disc plugs 32. An axially extending cooling passage 35 is formed between the inner end surface 37 of the base end 24 and the actuator 16. The passageways 35 are there for freezing air through the slots 26, one anterior annular space 31, the anterior side of the disc 16 within one anterior annular space 33 the anterior 16 the outermost 16 flap mounts 24, the disc ears 32 and the active rim 39 of the disc 16. * A portion flowing through the cooling air passages 35 diverges within the cooling air passages or compartments 23 through the inlets 20 through the channels 27, through the ends of the flap bases 24. The channels 27 have inlets 35 through the communication 29 through the slits 26.
The second rotor assembly 14 comprises a disc 34 having many blades 36 abutting peripherally around its periphery. * As you can see better in Figs.
and 3, each flap 36 comprises a base portion 40 and a spacer portion 38 having a cross-platform 42.
The base portion 40 comprises a fir-shaped end-base 44 arranged within a similar fir-like shape 46, the rats forming between the tray ears 47. The slots 46 extend axially through the tray 34, from the front face 50 to the front side 48. The innermost radially inwardly facing surface 51 of each base end 44 is radially apart from radially inwardly <sub>f</sub> Outside swivel surface - hit 53 of slot 46, that
7 is also an active rim of the disc 34. A first axially extending cooling air passage 55 is formed between the freezing air through the disc slot 46 of a six-compartment, e.g. partition 66 on the front side of the disc 34, in an annular space 57 on the rear side of the disc 34. * Other aspects of the second step cooling and the blades will further be described.
The discs 16.34 are connected to a shaft assembly of the machine 52 by means of an annular support member 54, which is threaded to the shaft assembly 52, e.g. 56. In particular, the disc 16 comprises a flanged cylindrical support arm 58, and the disc 34 comprises a flanged cylindrical arm 60. The flanged arms 58,60 are secured to the supporting members e.g. with many nut and screw assemblies 62.
* In annular spacer 64 is inserted radially outward of the flange mounting brackets 58.60 and extends axially between the rear 30-degree rear disc 16 and the rear rear end 48 radially outwardly of the support arms, each extending axially between the rear face 30 and the front face 48. The front end 68 of the spacer piece 64 comprises a radially outwardly rotating cylindrical surface 70, which is disposed with a corresponding radially facing inwardly directed nr
-9A annular wing retaining plate 90 is mounted at the front view 28 of disc 16. In particular, the radially inner end 92 of the plate 90 comprises an axially extending flange 94, having a circumferential circumference 94 28 of the disc 16 comprises an axially extending flange 98 having a radially inwardly rotating cylindrical surface 100. * Surface 96 matches surface 100 to orient and support plate 90 radially to disc 16. Plate 90 is axially trapped in its position with a ring slot 101 and at a corner 102 in a radially extending inward flange 104 of disc 16, e.g. with screws 106. * The sealing brace 102 comprises many classical and radially extending outer knife blades 103, having a sealing relationship with a static annular sealing region 110, which is secured to a substantially static spindle structure.
* Plate 90 also comprises an axially extending cylindrical sealing carrier 114, folded therewith, and carrying many classical radially outwardly extending knife edges 116. At these edges 116 are stamped in a sealed area with a seal 118 112. The static structure 112 cooperates with a stationary stator blade stage 120, which are arranged in the gas-to-anti-roll path.
<img file="GR82527B_D0002.tif" />
-10th rotor blades 20. The fixed blades 120 are secured by suitable means to the outer shell of the machine 88.
* Plank 90 further comprises an intercellular portion 126 extending radially outwardly downstream. The frustoconical portion 126 has a radially outer outer end 128. The end 128 comprises an annular surface 61 rotated downstream, supporting the anterior edge 28 of the tray 16 and the outermost aperture 24. 1, sealing carriers 102,104, or plugs 90 and or static structure 112 define an inner annular compartment 122, in which cooling air is supplied by many peripherally spaced nozzles 124. Plate 90 between the inner and outer edges of the limbs, and the 128, lies away from the front face of the trays 28 which defines the annular space of the air cooler 31, which is in communication through the large lugs 122 through 132. and that was really part of it. Knife edges 116 and a sealing wire 134 between plate end 128 and disk tray 28 prevent the outflow of compartments 122.31 radially outwardly within an outer gas compartment 136.
Many blade segments 138 are secured to the rear side 30 of the first disc 16 and are arranged peripherally around the shaft of the machine. In one of these flap seating segments 138 is shown prospectively in Fig. 5. Each segment 138 comprises an oppositely rotated surface surface 140,142. Oh, yeah
A r
-11 surface 140 is supported by the extreme surface 142 of adjacent sectors, to form a complete annular member consisting of sectors. The segments 138 are trapped axially between the spacer 64 and the rear face 30 of the first tray 16, to determine said rear annular cooling chamber 33, comprising the cooling air 35 . An anteriorly curved and circumferentially extending surface 154 adjacent to the radially outer edge 146 of each sector 138 is provided against the disc view 30 (indeed against the ears 32) and at the distal ends of the outer limbs or which is improved by a sealing wire 156 arranged in an annular groove formed by arcuate groove sections 158 in each flap retaining portion 138. Likewise, at the rear facing arcuate section 160 is held against the anteriorly rotating annular 162 of the spacing piece 64 and, with a sealing wire 164, arranged therein form a complete annular seal against the surface 162.
* Each end panel 140, 142 is retracted or has a staircase up to 148 to form a surface 150 parallel to the plane of the corresponding end panel 140.1142. At present 150 are exposed from the inner edge 144 of the section 135 to the tier 143. The slits 152 are formed below, as shown
-12 better in Fig. 4- between sloping segments 138. Slits 152 provide a fluid flow communication between the gas compartment 133 and the bulk compartment 66, by said insect-metered flow 71 at the forward end 68 thereof Measuring Sticks 151 (Fig. 4) formed between flushing segments 138 provide fluid flow communication between the gas space 33 and the outer annular compartment 153; * The cooling air compartment 153 is used to cool the blade edges 80 and the seal area 82.
The flap retainer segments 138 are supported and positioned radially by an anteriorly extending arcuate lip 163 having a radially outwardly facing surface 170, that is, by a radially upwardly rotating interior 17. is woven with a diagonally extending annular flange 176 of disc 16, to further suitably accommodate the segments 138 axially and radially to the disc 16.
* The second tier disc 34 also has flaps retaining means at its anterior and posterior sides. In this construction, the spacer 64 is also provided with a front flap retainer. In particular, the rear end of the spacer 64 comprises a radially outwardly extensible wraparound plate 178, having a rear surface 130 that is oblique to the front surface 40 and 47.
-13Al these front surfaces are roughly flat. The overlap 178 extends radially outwardly to the wing platform 42 to cover or close the front end of the space or volume 186 by defining between the extending portions 187 and 40.
A rear annular overlapping plate 188 blocks the axis to the rear movement of the blades.
The rear overlap 188 has an annular frontally extending lip 170, which is applied to a step 192 on the rear side of the disc 34, thereby mounting and mounting radially or overlap. * The back coating plate is trapped axially by a split annular ring 193 "whoever contacts the radially esotatin acrania the cover 183 and applied tightly between These and a radially prds outwardly extending annular flange 194 of the disc 34. The radially outermost end 196, cover plate 188 includes an anteriorly rotated surface annular 198, which *
Forms an annular seal against approximately planes and to the rear faces of the disc ears 47 and to the rear faces of the flaps base edges 198. Between the aperture 19 and the aperture diameter 19 It is axially apart from the rear face 50 of disc 34, to determine said annular gas space 57 between them.
* As shown best in Figs.
radially inwardly facing surfaces of 200 outer zones "Z" with teeth 202 in the segment up to 40 radially outward from their respective opposing surfaces 204 in the inner ear 206 for fixing second cooling air passages 208 through the slots 46. These passages have inlets 209 in the rear face 50 of disc 34, causally communicating with the gas compartment 57. The radially outermost portion of the front face of each ear 47 is slightly cut back, such as 210, to be slightly distant from the surface 180 of the overlap 173, to provide fluid communication between the outer bushes 21 and 18 between the flap base sections 40.
At first the cooling air passages 55 have inlets 212 and outlets 214. At the inlets 212 are slotted 75.77 with the coolant intermediate compartment 66 between the first and second rotor disc 16.34. At outlets 214 open to the gas compartment 57 on the bottom side of the disc 34. At the first passages and second passages 55,208 lie in a fluid flow sequence relationship through the gas compartment 57. Since the pressure in the intermediate compartment 66 is greater than the pressure in the spaces 186, the cooling air flows out of the compartment 66 through the first passages 55 in the gas compartment 57, and then in the opposite direction through the directional direction. 208. Then air flows into sites 186 through the insects 210 and 47. Out of space 186d refrigerant air flows into a compartment (not shown) downstream of the AX-AX 210 having such a size as to be measured or refrigerant flow V *;
-15 air through the base slots of the blades 46.
Referring to Figures 6 and 7 of a preferred embodiment, the second-stage aerosomes 58 have cooling passages or compartments 215 which are fed with cooling air from the intermediate compartment 66 between the tray 16, 34 through a radially 21 flap base portion 40. The channel 216 interconnects the flap compartments 215 with the first cooling passage 55 via the base slot 46. An inlet 21S through channel 216 is covered by a thin plate 220. * The plate 220 has a metered supply opening 222 aligned with the inlet 213, to measure the appropriate amount of flow from the first passage 55 through 55 The air compartments 215 leave the airfoil through holes and slots (not shown) through the airfoil wall, to cool it as is well known in the art. During operation of the rotor, the pressures in the compartments 215 are less than the pressure in the coolant intermediate compartment 66, so that the air flow is directed in the appropriate direction.
Examining the turbine section 10 as a whole, we find that a new cooling device has been provided by means of a six-compartment cooling compartment against the first-stage rotor disc 16 used to cool the first, second, and lateral discs. flap and spoilers. 'The construction of this turbine sector is particularly unique as it does not have a hinge limiting its life span.
-16 first disc, for cooling air from the downstream to the second-stage blades and to the second-stage aerosol 38. Further, the single-stage dual-stage cooling air flow device mass of cooling air to cool the second-stage disc rim, the ears and the fin blades, by 26%.
If an invention has been shown and described in connection with a preferred embodiment, those skilled in the art will understand that various other alterations and omissions can be made in such a manner and detail without any exception.
Contents2
4 sheets
Sheet 1 Sheet 2 Sheet 3 Sheet 4
19 members in 14 offices
Priority claims4
| Document | Office | Kind | Date |
|---|---|---|---|
| 56445483 | United States of America | A | |
| 56445483 | United States of America | A | |
| 564454 | – | – | – |
| US19830564454 | – | – | – |
Members19
| Document | Office | Kind | |
|---|---|---|---|
| DK599084D0 | Denmark | D0 | |
| GB8431269D0 | United Kingdom | D0 | |
| GR82527BThis record | Greece | B | |
| IL73764A0 | Israel | A0 | |
| BE901368A | Belgium | A | |
| DK599084A | Denmark | A | |
| FR2557206A1 | France | A1 | |
| DE3444586A1 | Germany | A1 | |
| KR850004511A | Republic of Korea | A | |
| NL8403845A | Netherlands (Kingdom of the) | A | |
| GB2151715A | United Kingdom | A | |
| JPS60156903A | Japan | A | |
| US4582467A | United States of America | A | |
| CA1209482A | Canada | A | |
| GB2151715B | United Kingdom | B | |
| CH667896A5 | Switzerland | A5 | |
| TR23227A | Türkiye | A | |
| IL73764A | Israel | A | |
| FR2557206B1 | France | B1 |
Numbers
- Publication, DOCDB
- 82527
- Publication, EPODOC
- GR82527
- Application
- 82527
- Application, DOCDB
- 840182527
- Application, EPODOC
- GR19840182527
Titles
- English
- TWO STAGE ROTOR ASSEMBLY WITH IMPROVED COOLANT FLOW
Classification
- CPC, 3
- F01D5/081
- F02C7/12
- F01D5/3015
- IPC, 3
- F01D5 08
- F01D5 18
- F01D5 30
