EP0236337B1 - Seal ring means for a bladed rotor assembly - Google Patents
Seal ring means for a bladed rotor assembly Download PDFInfo
- Publication number
- EP0236337B1 EP0236337B1 EP19860901729 EP86901729A EP0236337B1 EP 0236337 B1 EP0236337 B1 EP 0236337B1 EP 19860901729 EP19860901729 EP 19860901729 EP 86901729 A EP86901729 A EP 86901729A EP 0236337 B1 EP0236337 B1 EP 0236337B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- rotor
- ring segment
- spacer
- blades
- slot
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired
Links
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
- F01D5/3015—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type with side plates
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
- This invention relates generally to gas turbine engine rotors and more particularly to the device for retaining the blades of a bladed rotor against axial movement on the rotor, sealing the gaps at the roots of the blades, dampening blade vibration and to the method of assembling the retaining device.
- Turbine rotor assemblies having removable blades have been used in gas turbine engines and turbochargers to reduce cost and increase serviceability over one-piece rotors. The ability to replace worn or damaged blades rather than replacing the entire rotor has allowed the engineer to strive for greater efficiency by reducing the gap or space between the tip of the turbine blade and the surrounding shroud. However, during actual operation of the engine, thermal variation (expansion from heat and retraction from cooling) at start-up and running modes will vary the clearance and efficiency.
- The current rotor assemblies consist of a forged rotor hub which is machined to accept a plurality of individual blades. The root portion of the blades are assembled on the hub to prevent centrifugal force from extracting the blade from the hub. A seal ring is attached to the hub to prevent the blades from moving axially out of the hub and to prevent the passage of working gases between the hub and the root portion of the blade. By blocking the space between the root portion of the blade and the hub, the seal causes all the working gas to pass through the working portion of the blade and increases the operating efficiency of the engine.
- A large variety of structures and methods have been devised to attach the seal ring to the rotor. US-A-3,807,898 discloses a bladed rotor assembly which has a segmented sealing plate, a groove in the blades, a half-round groove in the plate segments, and a half-round groove which cooperates with the half-round groove in the segments. The blades are assembled in the rotor; the segments are inserted in the groove of the blade and a lock wire is circumferentially inserted into the two half-round grooves. The seal plate retains the blades in position and seals the flow of working gas from passing between the rotor and the blades. The segments overlap one another to prevent leakage past the segments. US-A-4,344,740 discloses a rotor assembly which consists of a plurality of attaching slots and lugs on the disk, a plurality of blades equal in number to the slots and a one-piece sideplate has lugs thereon. The sideplate is positioned on the rotor with the blades secured in the slots, and the lugs on the rotor and the lugs on the sideplate interleaved. The sideplate is forced against the rotor, the lugs are caused to elastically deform and the sideplate is rotated until the lugs on the sideplate are captured beneath the lugs on the rotor. An antirotation pin is used to prevent relative movement between the sideplate and the disc. Furthermore, US-A-4,523,890 discloses an end seal for a turbine blade base. The seal consists of a seal ring and a plurality of seal plate segments. The seal ring is positioned between the seal plate segments and the blade at one end, and between the seal plate segments and the turbine wheel at the other end. After installation of the seal ring each of the seal plate segments are conventionally installed.
- The disadvantages of the above noted rotor assembly constructions are that they increase the manufacturing cost, are difficult to service, and reduce the dependability of the rotor assembly. For example, US-A-3,807,898 involves increased manufacturing and assembly costs by requiring two half-round grooves and two lock wires which must be fed into the two half-round grooves and bent radially inwardly to prevent the wire form passing too far into the groove. US-A-4,344,740 involves increased manufacturing and assembly costs by using a plurality of lugs on both the rotor and the sideplate. The lugs require machined tapers to mate with each other and the assembly technique requires special tooling such as heating facilities and a press. US-A-4,523,890 involves increased manufacturing and assembly costs due to the addition of a complex shaped seal ring and a complex machining configuration of the turbine wheel retainer area. The above patents describe expensive bladed rotor assembly employing complex machining and assembly techniques. The seal ring must be removed from the rotor to replace a single failed blade and then requires that the complex assembly technique be followed to reassembly.
- In accordance with the invention, a bladed rotor assembly comprising a rotor having opposed faces, a rim and a plurality of circumferentially arrayed retention slots in the rim, the slots passing from one of the faces to the other of the faces and having radial retention means, a plurality of blades mounted on the rotor with each of the blades having a root portion received in a corresponding one of the slots, the root portion being shaped so that it engages the radial retention means to prevent movement of the blade radially outwards of the rotor; means on the rotor and on each of the plurality of blades for defining an annular T-slot at one of the faces; means defining an opening in the means on the rotor which forms a portion of the T-slot; seal means rotatably trapped in the T-slot and including ring segment means having first and second ends circumferentially spaced apart to define therebetween a space wide enough for the passage of a blade root portion, and a spacer positioned between the ends of the ring segment means, the arcuate length of the opening being at least equal to the length of the spacer, and the seal means being indexable to a position at which the spacer is out of alignment with the opening in the rotor; and means for preventing rotation between the seal means and the rotor; (as disclosed in GB-A-905582); is characterised in that the ring segment means comprises a single ring segment.
- The invention also includes a method of assembling a bladed rotor assembly, the rotor assembly including a rotor having opposed faces, a rim and a plurality of circumferentially arrayed retention slots in the rim, the slots passing from one of the faces to the other of the faces and having radial retention means; and a plurality of blades mounted on the rotor with each of the blades having a root portion received in a corresponding one of the slots, the root portion being shaped so that it engages the radial retention means to prevent movement of the blade radially outward of the rotor; means on the rotor for forming a circumferentially extending, radially outwardly facing groove on the rotor; and means on each of the plurality of blades for forming a circumferentially extending inwardly facing groove; the method comprising the steps of:
- a) positioning a ring segment means in the groove formed in the rotor, so that a space defined between circumferentially spaced apart first and second ends is aligned with one of the slots in the rotor;
- b) inserting the root portion of a blade through the space in the ring segment means and into one of the slots in the rim so that an arcuate portion of an annular T-slot is formed;
- c) indexing the segment means into the arcuate portion of the T-slot to align the space in the segment with another one of the slots in the rotor;
- d) inserting the root portion of a second one of the plurality of blades through the space in the ring segment means and into the another one of the slots in the rim so that the arcuate portion of the annular T-slot is increased in length; and
- e) progressively repeating steps c) and d) until all of the retention slots contain a blade; closing the space so that no blade is retractable from its slot; and fixing the ring segment means against further indexing in the T-slot; (as disclosed in FR-A-1580473);
is characterised in that the ring segment means comprises a single ring segment which is initially positioned in the groove; in that the space is closed by a spacer which is introduced through an opening in the groove-forming means on the rotor with the space aligned with the opening, the spacer and the ring segment means being indexed until the spacer is trapped in the T-slot; and in that a hole extending through one of the spacer and ring segment is aligned with a hole in the face of the rotor and means are inserted in the hole for preventing further indexing between the seal means and the rotor. - The present invention provides a simple and inexpensive method of replacing individual worn or damaged blades of a rotor assembly. The means for preventing rotation are removed and the seal means which is rotatably trapped in the T-slot is indexed so that the ends of the ring segment means align with the opening in the rotor and the spacer is removed. The ring segment means is rotated until the ends align with the worn or damaged blades to be removed and replaced. After replacing the blades, the ring segment means is indexed to align the ends with the opening and the spacer is inserted, the seal means is indexed to a position at which the spacer is out of alignment with the opening in the rotor, and the means for preventing rotation is secured to the rotor. The present invention provides for a simple and inexpensive means to attach a plurality of blades to a rotor while providing a seal to ensure the flow of working gases through the working portion of the turbine blades and for dampening blade vibration. The assembly technique is simple and easy to employ. The use of heavy presses for assembly or disassembly and complex machining configuration have been eliminated. The present invention is simple to employ, allows for the flexibility of replacing a single or a plurality of worn or damaged blades and does not require a complexity of machining or assembly fixtures.
- In the accompanying drawings:
- Figure 1 is a view of a gas turbine engine employing the present invention;
- Figure 2 is an end view of a rotor assembly constructed in accordance with the present invention; and
- Figure 3 is a sectional view along lines III-III of Fig. 2 showing a detailed view of the rotor, blade and ring means.
- Referring to Figure 1, a
bladed rotor assembly 10 is shown in agas turbine engine 12. As shown in Figure 2, therotor assembly 10 comprises a rotor 14, a plurality ofblades 16, means 18 on the rotor and on each of the plurality of blades for defining an annular T-slot 20, means 22 defining anopening 23 in the rotor 14 to provide access to a portion of the T-slot 20, means 24 for sealing positioned in the T-slot 20 and means 26 for preventing relative rotation between themeans 24 for sealing and the rotor 14. - The rotor 14, as shown in Figures 2 and 3, has a
center hub 28 and arim 30 at its perimeter. A web 32 connects thehub 28 to therim 30. The rotor 14 has opposite first andsecond faces first face 34 is stepped or multilevel, a plurality ofblind holes 38 in thefirst face 34 and a plurality of circumferentially arrayedretention slots 40 positioned in therim 30. Theslots 40 extend from oneface 34 to theother face 36 and have a radial retention means 42 which includes a pair ofside walls 43 which are undercut in a conventional manner to provide at least one inwardly directedabutment face 44 on each side wall. - The plurality of
blades 16 are mounted on the rotor 14. Each of the plurality of blades has aroot section 46 which engages acorresponding slot 40 and is spaced away from abottom 50 of theslot 40 in the rotor 14. Theroot portion 46 is shaped so that it engages theabutment face 44 of the rotor 14. Eachblade 16 has aplatform section 52 disposed radially outwardly from the periphery of therim 30 by anextended neck region 54 of theblade 16. Each blade has alip 56 projecting radially inward from theroot section 46 and abuts a portion of the multilevel surface of thefirst face 34. - The
means 18 on the rotor 14 for defining a portion of the T-slot 20 includes a circumferentially extending radially outwardly facinggroove 62 which extends axially outward from thefirst face 34 of the rotor 14. Themeans 18 on eachblade 16 for defining a portion of the T-slot 20 includes a circumferentially extending radially inwardly facinggroove 64 formed on eachblade 16 intermediate theroot section 46 and theplatform section 52 and on the same side as thelip 56. - The opening 23 in said means 18 on the rotor 14 which forms a portion of the T-
slot 20 opens into thegroove 62 and has an arcuate length D2 for purposes to be defined later. - The
means 24 for sealing includes a ring segment means 74 having first andsecond ends space 80 therebetween, and a segment shapedspacer 82 positioned in thespace 80. Thespacer 82 has a circumferential length slightly less than the circumferential length of the space to define a controlledgap 84 or clearance between thespacer 82 and on both of theends opening 23 is at least equal to the length of thespacer 82. - The ring segment means 74 is a
single ring segment 86 with theends - The ring segment means 74 and the
spacer 82 each have aninner edge 88 and anouter edge 90. Theinner edges 88 are received in the outwardly facinggroove 62 of the rotor 14 and theouter edges 90 are received in the inwardly facinggroove 64 of eachblade 16. Theinner edge 88 of the ring segment means 74 has aninner leg portion 92 which is angled away from thefirst face 34 on the rotor 14 and theouter edge 90 has anouter leg portion 94 which angles away from theroot portion 46 of theblade 16. The means 26 for preventing relative rotation between the means for sealing 24 and the rotor 14 as shown in Fig. 2 includes ahole 100 extending through one of thespacers 82 and ring segment means (74), one of theblind holes 38 in the first face of the rotor 14, and apin 102 having a diameter slightly smaller than theholes pin 102 has a hollow recess in one end. As an alternative, thepin 100 could be a rivet or a bolt inserted through theholes 100 in thespacer 82 and the blind holes would be through drilled in rotor 14. - The
bladed rotor assembly 10 is preassembled prior to assembly into agas turbine engine 12. Thesingle ring segment 86 is assembled into thegroove 62 by spreading theends single ring segment 86 over the rotor and releasing the ends with thesingle ring segment 86 positioned in thegroove 62. As an alternate, one end of thesingle ring segment 86 could be inserted through theopening 23 in the rotor 14 and threaded around thegroove 62 so that theinner leg portion 88 of thesegment 76 is trapped within thegroove 62 in the rotor 14. Thespace 80 between the first and second ends 76, 78 of thesegment 86 is aligned with one of theslots 40 in therim 30 of the rotor 14 so that theroot portion 46 of theblade 16 will pass therethrough. Theroot portion 46 of one of the plurality ofturbine blades 16 is inserted into thatslot 40 from thefirst face 34 side until thelip 56 contacts thefirst face 34. With theblade 16 in theslot 40, thegroove 64 is radially aligned with thegroove 62 to form a short portion of the T-slot 20. At this point, thesegment 86 is indexed to align thespace 80 with another of theslots 40 in the rotor 14. In so doing, a portion of thesegment 86 enters the short portion of the T-slot and locks the blade to the rotor in an axial direction. Theroot portion 46 of asecond blade 16 is then inserted into theslot 40 aligned with thespace 80 and thesegment 86 is again indexed to lock the second blade to the rotor 14 and thespace 80 is aligned with the next adjacent slot. The sequence of inserting ablade 16 in theslot 40 and indexing thesegment 86 is repeated until all theslots 40 contain ablade 16. Thesingle ring segment 86 is then rotated to align thespace 80 with theopening 23 in the rotor 14. Theleg portion 94 of theouter edge 90 of thespacer 82 is positioned in the inwardly facinggroove 64 formed by theblades 16. Thesegment 86 andspacer 82 are rotated within the T-slot 20 until thehole 100 in thespacer 82 aligns with one of theblind holes 38 in the rotor 14 at which position thespacer 82 is out of alignment with theopening 23 in the rotor 14 and thegap 84 is positioned so that the space between the rotor 14 and the bottom 50 of theblade 16 do not coincide. Thepin 102 is inserted through thehole 100 in thespacer 82 into theblind hole 38 in the rotor 14 with the hollow end toward the rotor and fixedly attached to the rotor 14 using a punch and a hammer. The hollow end is expanded in thehole 38 by tapping thepunch againstthe pin 102 with the hammer. - After completing the assembly, the
bladed rotor assembly 10 will be assembled by a conventional manner into agas turbine engine 12. During operation of thegas turbine engine 12, heat is absorbed in thethin spacer 82 and thesingle ring segment 86 at a high rate wherein the mass of the rotor absorbs heat at a slower rate. Therefore, the controlledgap 84 between thesingle ring segment 86 and thespacer 82 will be filled due to the difference in the rate of heat absorbed in the masses in the start up mode. As the engine continues to warm up and enters the steady state mode, the controlledgap 84 will reoccur. - The primary advantage of the
bladed rotor assembly 10 of this invention is in the unique construction of the ring segment means 74 and thespacer 82, and the simple assembly technique which can be used to make a new rotor or repair a damaged rotor. For example, when thebladed rotor assembly 10 has a failedblade 16 and requires that the blade be replaced therotor assembly 10 will be removed from the engine using conventional disassembly techniques. Thepin 102 which prevents the means for sealing 24 from rotating relatively to the rotor 14 is removed. The ends 76, 78 of thesingle ring segment 86 are aligned with theopening 23 in the rotor 14 and thespacer 82 is removed from the inwardly facinggroove 64 formed by theblades 16. The ends 76, 78 of thesingle ring segment 86 are rotated to align with the damagedblade 16, theblade 16 is removed from theslot 40 in the rotor 14 and anew blade 16 is replaced in theslot 40. Thesingle ring segment 86 can be rotated to align with each damagedblade 16 and theblade 16 can be replaced. This process continues until all of the worn or damagedblades 16 are replaced. Thespacer 82 is repositioned and the pin or pins 102 are secured as discussed earlier. Thus a simple inexpensive repair to thebladed rotor assembly 10 can be employed when using the present invention.
Claims (7)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US77545185A | 1985-09-12 | 1985-09-12 | |
US775451 | 1985-09-12 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0236337A1 EP0236337A1 (en) | 1987-09-16 |
EP0236337B1 true EP0236337B1 (en) | 1989-03-01 |
Family
ID=25104469
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP19860901729 Expired EP0236337B1 (en) | 1985-09-12 | 1985-12-06 | Seal ring means for a bladed rotor assembly |
Country Status (5)
Country | Link |
---|---|
EP (1) | EP0236337B1 (en) |
JP (1) | JPS63500879A (en) |
CA (1) | CA1235071A (en) |
DE (1) | DE3568465D1 (en) |
WO (1) | WO1987001761A1 (en) |
Families Citing this family (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2603333B1 (en) * | 1986-09-03 | 1990-07-20 | Snecma | TURBOMACHINE ROTOR COMPRISING A MEANS OF AXIAL LOCKING AND SEALING OF BLADES MOUNTED IN AXIAL PINS OF THE DISC AND MOUNTING METHOD |
US4982272A (en) * | 1988-07-21 | 1991-01-01 | Magnascreen Corporation | Modular flat-screen color television displays and modules and circuit drives therefor |
US5079636A (en) * | 1988-07-21 | 1992-01-07 | Magnascreen Corporation | Modular flat-screen television displays and modules and circuit drives therefor |
US4980774A (en) * | 1988-07-21 | 1990-12-25 | Magnascreen Corporation | Modular flat-screen television displays and modules and circuit drives therefor |
US5068740A (en) * | 1988-07-21 | 1991-11-26 | Magnascreen Corporation | Modular flat-screen television displays and modules and circuit drives therefor |
GB9517369D0 (en) * | 1995-08-24 | 1995-10-25 | Rolls Royce Plc | Bladed rotor |
ATE441776T1 (en) * | 2007-01-09 | 2009-09-15 | Siemens Ag | AXIAL ROTOR SECTION FOR A ROTOR OF A TURBINE |
FR2939832B1 (en) * | 2008-12-11 | 2011-01-07 | Turbomeca | TURBINE WHEEL EQUIPPED WITH AXIAL HOLDING DEVICE LOCKING BLADES WITH RESPECT TO A DISK. |
EP3438410B1 (en) | 2017-08-01 | 2021-09-29 | General Electric Company | Sealing system for a rotary machine |
FR3127255A1 (en) * | 2021-09-23 | 2023-03-24 | Safran Aircraft Engines | Rotary assembly for turbomachine |
Family Cites Families (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB905582A (en) * | 1960-05-26 | 1962-09-12 | Rolls Royce | Improvements relating to the sealing of blades in a bladed rotor |
GB954323A (en) * | 1962-03-17 | 1964-04-02 | Rolls Royce | Improvements in or relating to bladed rotors for fluid flow machines such as turbines |
US3300179A (en) * | 1966-04-22 | 1967-01-24 | Gen Motors Corp | Blade stalk cover plate |
GB1095830A (en) * | 1966-09-13 | 1967-12-20 | Rolls Royce | Bladed rotor for a fluid flow machine such as a gas turbine engine |
GB1236920A (en) * | 1967-07-13 | 1971-06-23 | Rolls Royce | Bladed fluid flow machine |
FR2524933B1 (en) * | 1982-04-13 | 1987-02-20 | Snecma | AXIAL LOCKING DEVICE FOR TURBINE OR COMPRESSOR ROTOR BLADES |
-
1985
- 1985-12-06 EP EP19860901729 patent/EP0236337B1/en not_active Expired
- 1985-12-06 DE DE8686901729T patent/DE3568465D1/en not_active Expired
- 1985-12-06 WO PCT/US1985/002402 patent/WO1987001761A1/en active IP Right Grant
- 1985-12-06 JP JP86502153A patent/JPS63500879A/en active Pending
-
1986
- 1986-09-09 CA CA000517815A patent/CA1235071A/en not_active Expired
Also Published As
Publication number | Publication date |
---|---|
CA1235071A (en) | 1988-04-12 |
EP0236337A1 (en) | 1987-09-16 |
WO1987001761A1 (en) | 1987-03-26 |
JPS63500879A (en) | 1988-03-31 |
DE3568465D1 (en) | 1989-04-06 |
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