EP3495611B1 - Apparatus for controlled delivery of cooling air to turbine blades in a gas turbine - Google Patents
Apparatus for controlled delivery of cooling air to turbine blades in a gas turbine Download PDFInfo
- Publication number
- EP3495611B1 EP3495611B1 EP17205756.4A EP17205756A EP3495611B1 EP 3495611 B1 EP3495611 B1 EP 3495611B1 EP 17205756 A EP17205756 A EP 17205756A EP 3495611 B1 EP3495611 B1 EP 3495611B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- rotor
- row
- cooling air
- blades
- shield elements
- 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.)
- Active
Links
- 238000001816 cooling Methods 0.000 title claims description 37
- 238000007789 sealing Methods 0.000 claims description 5
- 238000011144 upstream manufacturing Methods 0.000 claims description 4
- 230000008878 coupling Effects 0.000 claims description 2
- 238000010168 coupling process Methods 0.000 claims description 2
- 238000005859 coupling reaction Methods 0.000 claims description 2
- 230000013011 mating Effects 0.000 claims 1
- 239000007789 gas Substances 0.000 description 31
- 239000000463 material Substances 0.000 description 4
- 241000218642 Abies Species 0.000 description 3
- 235000001674 Agaricus brunnescens Nutrition 0.000 description 2
- 230000007423 decrease Effects 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Images
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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/001—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between stator blade and rotor
-
- 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
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/08—Heating, heat-insulating or cooling means
- F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
-
- 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
Definitions
- the present invention relates to an apparatus for controlled delivery of cooling air to turbine blades in a turbine section of a gas turbine power plant.
- the present invention relates to an apparatus for controlling cooling air delivery to rotor heat shield cavities to protect the rotor material against hot gas.
- a gas turbine for power plants comprises an upstream compressor, a combustor assembly and a downstream turbine.
- the turbine includes a rotor comprising a compressor section and a turbine section.
- downstream and upstream refer to the direction of the main gas flow passing through the gas turbine.
- the compressor comprises an inlet supplied with air and a plurality of blades compressing the passing air.
- the major part of the compressed air flows into a combustor where the compressed air is mixed with at least one fuel. This mixture is combusted in the combustor leading to a significant temperature rise.
- the resulting hot gas leaves the combustor and is expanded in the turbine, producing mechanical work on the rotor.
- Devices called rotor heat shields (RHS) are generally inserted between two adjacent blade rows to form cavities that can be supplied with cooling air.
- An object of the present invention is to provide an apparatus for controlled delivery of cooling air to turbine blades in a gas turbine which addresses the above problems.
- Lock plates 42 have hooks 51 configured to couple lock plates 42 to rotor unit 4.
- two hooks 51 are arranged at opposite radial edges of the lock plate 42 in the proximity of the outer edge and engage with lugs 52 of the rotor unit located at opposite sides of each firtree seat 16.
- cooling air is fed through passage 37 into passage 38; part of this flow is used to cool blades 5 of row 6 internally, as known per se.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Description
- The present invention relates to an apparatus for controlled delivery of cooling air to turbine blades in a turbine section of a gas turbine power plant. In particular, the present invention relates to an apparatus for controlling cooling air delivery to rotor heat shield cavities to protect the rotor material against hot gas.
- As is known, a gas turbine for power plants (in the following, "gas turbine" only) comprises an upstream compressor, a combustor assembly and a downstream turbine. The turbine includes a rotor comprising a compressor section and a turbine section.
- The terms downstream and upstream as used herein refer to the direction of the main gas flow passing through the gas turbine.
- In particular, the compressor comprises an inlet supplied with air and a plurality of blades compressing the passing air. The major part of the compressed air flows into a combustor where the compressed air is mixed with at least one fuel. This mixture is combusted in the combustor leading to a significant temperature rise. The resulting hot gas leaves the combustor and is expanded in the turbine, producing mechanical work on the rotor.
- While the turbine blades are made of a material designed to withstand the hot gas temperatures, and thus costly, the rotor is generally made of a less costly material with a lower resistance to high temperatures. Therefore, a flow of cooling air must be provided in the rotor section, below the hot gas path, to protect the rotor material against the hot gas temperature. Devices called rotor heat shields (RHS) are generally inserted between two adjacent blade rows to form cavities that can be supplied with cooling air.
- In the turbine section, the hot gas pressure decreases from one blade row to the following. It is known in the art that the pressure of the cooling air supplied to the individual blades rows at the root of the blades should be above the hot gas pressure at that blade row to avoid leakage of hot gas into cooling cavities; however, the cooling air pressure should not be too high in order to avoid excessive flow of cooling air into the hot gas path, which would reduce efficiency.
- Controlling cooling air delivery is even more complex when air is supplied to two blade rows from a single source.
-
US2010/0074732 discloses a gas turbine sealing apparatus having the features of the preamble of claim 1. - An object of the present invention is to provide an apparatus for controlled delivery of cooling air to turbine blades in a gas turbine which addresses the above problems.
- According to a first aspect of the present invention, the apparatus includes:
- a plurality of rotor heat shield elements disposed in a circumferential row between a first and a second row of turbine blades, each shield element having a root portion contoured so as to fit in a seat of the rotor unit, an intermediate radial portion and a shroud band configured to be axially interposed between platform portions of the turbine blades of the first and second turbine blade row, the rotor heat shield elements configured to define with a rotor unit of the turbine a rotor heat shield passage that is fed with cooling air; and
- at least a row of lock plates configured to secure axially at least one of said first and second rows of turbine blades to said rotor unit, said lock plates facing said rotor heat shield elements,
- a first cavity between by the first row of turbine blades and the radial portion of the shield elements and a second cavity between the radial portion of the shield elements and the second row of turbine blades,
- According to the invention, pressure drop along the different portions of the rotor heat shield passage can be controlled so as to ensure optimum local balance with the pressure of the hot gas.
- According to an embodiment, two portions or cavities of the rotor heat shield passage communicate through the aperture in the radial portion of the rotor heat shield elements, which allows to control pressure in the two portions even though only one of them is supplied with cooling air.
- In an embodiment, the rotor shield elements include at least one feature configured to cooperate with an axial finger extending from the platform portion of the blades of at least one row in order to lock said rotor shield elements circumferentially; the opening is facing the features of the rotor shield elements, so that it can be used to receive the finger of a respective blade.
- Advantageously, lock plates are provided with hooks for coupling with said rotor unit; this makes assembly easy and quick.
- According to a preferred embodiment, the apparatus includes at least one, and preferable all, of:
- a circumferential wire seal between the root portions of the said rotor heat shield elements and said rotor unit,
- a circumferential wire seal between said lock plates and said rotor unit,
- circumferential seals between the shroud bands the said blades, and
- axial seals between each pair of adjacent shroud bands.
- This allows to reduce, and preferably eliminate, any undesired leaking paths for the cooling air.
- According to another aspect, the invention relates to a gas turbine including:
- a rotor unit;
- at least a first plurality of turbine blades disposed in a first circumferential row around the rotor unit and secured thereto,
- at least a second plurality of turbine blades disposed in a second circumferential row around the rotor unit and secured thereto,
- the first row and the second row being axially spaced with respect to one another, and
- an apparatus for controlled delivery of cooling air to turbine blades as defined above.
- For a better comprehension of the present invention, a preferred embodiment thereof will be described hereafter, by way of a non-limiting example and referring to the attached drawings, where:
-
Figure 1 is a partial axial cross section of an apparatus for controlled delivery of cooling air to turbine blades according to the present invention; -
Figure 2 is an enlarged view of a portion offigure 1 ; -
Figure 3 is a detailed view of another portion offigure 1 ; -
Figure 4 is a side view, partly sectioned, of a turbine blade of a gas turbine including the apparatus; -
figure 5 is an axial view from one side of a detail offigure 4 ; -
Figure 6 is ax axial view from an opposite side of a detail offigure 4 ; -
Figure 7 is a perspective view of a component of the apparatus of the invention; and -
Figure 8 is partial cross-section taken along line VIII-VIII infigure 1 . - Referring now to
figure 1 , a gas turbine 1 (only partially shown) includes arotor 2 rotatable about a rotor axis (not shown) and astator 3. - As is well known in the art,
rotor 2 includes arotor unit 4 and a plurality ofturbine blades 5 secured to therotor unit 4 and disposed in a plurality ofcircumferential blade rows figure 1 , but the number of blade rows is typically larger than three.Stator 3 is provided with a plurality ofturbine vanes 9 disposed in a plurality ofcircumferential vane rows respective blade rows figure 1 , but the number of vane rows is typically larger than three. The inner tip of thevane 9 is integrally connected to aninner vane platform 14 that extends circumferentially until the adjacent vane platforms; the gaps between twoadjacent vane platforms 14 is sealed with a seal. -
Blades 5 have, each, a firtree shapedshank portion 15 that is inserted in afirtree seat 16 of rotor unit 4 (fig. 6 ), aplatform portion 17 and anairfoil 18. -
Blade rows rotor unit 4 hasannular recesses - Turbine 1 also includes a plurality of rotor heat shield elements 23 (hereinafter, for brevity sake, RHS elements) disposed in
circumferential RHS rows - Each RHS element 23 (
figures 1-3 ) comprises a mushroomshaped root portion 26 engaged in an undercut mushroom shapedannular seat 27 at the bottom of the respectiveannular recess radial portion 28 and acircumferential shroud band 29. Theshroud bands 29 of theRHS elements 23 in each row are joined to one another by axial seals (not shown) to form a substantially continuous annual band, that is sealed circumferentially to each of the adjacent blade rows by means ofcircumferential seals 30.Root portions 26 are sealed against the bottom ofannular seat 27 by acircumferential wire seal 39. - A radial
small bore 56 in therotor unit 4, opening into the undercut portion of seat 27 (fig. 3 ), allows to insert a control wire (not shown) to check whether the circumferential position of RHS elements is correct, as shown e.g. inUS 2008/0181778-A . -
Shroud bands 29 have preferably a plurality of inclined sealingfins 31, which are alternatingly lower and higher and projecting outwardly to cooperate at a short radial distance with a steppedinner sealing contour 32 ofinner ring 14 of the stator. This reduces unwanted hot gas leakage betweenrotor 2 andstator 3. - As shown in
figures 2, 3 , theRHS elements 23 ofrows adjacent blade rows RHS cavity 33 via apassage 37 inrotor unit 4 which opens into apassage 38 through blade row 6 (fig. 2 ). -
Blades 5 are axially blocked bylock plates corresponding seat 45 onrotor unit 4 and a radiallyouter edge 46 engaging acorresponding seat 47 in the respective blade 5 (fig. 2 ). - As shown in
figure 2 and 3 ,radial portions 28 ofRHS elements 23 and/or lock plates 40-43 may includeapertures adjacent cavities apertures 48 inradial portion 28 ofRHS elements 23connect cavity 33 tocavity 34 andcavity 35 tocavity 36.Apertures 49 inlock plates 41 control air flow betweencavity 34 andpassages 38 throughblade row 7. -
RHS elements 23 are locked in a circumferential direction byaxial fingers 50 extending fromblades 5 and engagingcorresponding features 60 ofRHS elements 23, as known per se e.g. fromUS 2008/0181778-A . Such features may include a seat of any kind, e.g. a space between two projections ofRHS elements 23. - As shown in
figures 4 and 5 ,lock plates 42 have the shape of an annulus sector and are placed side by side in a circumferential row. Preferably, inner edges 44 are sealed with respect toseat 45 by means of awire seal 61 that is housed within agroove 62 inlock plates 52 and cooperates axially with one side of seat 45 (see enlarged detail infig. 4 ). -
Lock plates 42 are provided with a preferablyrectangular aperture 49 which, in addition to controlling the flow of cooling air as described previously, has the function of allowing acorresponding finger 50 to pass through (fig. 3 ,4 ). -
Lock plates 42 havehooks 51 configured to couplelock plates 42 torotor unit 4. Preferably, twohooks 51 are arranged at opposite radial edges of thelock plate 42 in the proximity of the outer edge and engage withlugs 52 of the rotor unit located at opposite sides of eachfirtree seat 16. - Lock plates 41 (
figures 4 and6 ) have preferably a substantially trapezoidal shape with a longer base connected torotor unit 4 and a shorter base connected to arespective blade 5. -
Lock plates 41 have a central cut-outopening 52 delimiting aflexible tab 53 which is bent axially towards therespective blade 5 so as to exert an elastic force thereon and recover axial play. -
Lock plates 41 also have anopening 54 close torotor unit 4 so as to allow cooling air flow at the blade roots. -
Blades 5 ofrow 6 haveplatform portions 17 extending radially outwardly of theshroud bands 29 ofRHS elements 23 ofRHS row 24.Platform portions 17 include shiplap seal features 55 (fig. 8 ) configured to cooperate with corresponding features of an adjacent blade so as to avoid gas leakage therebetween. - In use, cooling air is fed through
passage 37 intopassage 38; part of this flow is used to coolblades 5 ofrow 6 internally, as known per se. - The remaining part of cooling air is fed from
passage 38 intocavity 33, and hence tocavity 34 throughapertures 48 inradial portions 28 ofRHS elements 23. Cooling air than flows fromcavity 34 throughapertures 49 in lock plates intopassages 38 throughblade row 7; part of the flow coolsblades 5 ofrow 7 internally, as known per se. - Finally, cooling air flows through
apertures 49 oflock plates 42 intocavity 35, and hence intocavity 36 throughapertures 48 ofRHS elements 23. - The cross section of
apertures cavities
wherein one of said first and second cavity is supplied by a source of cooling air, the other of said first and second cavity being supplied with cooling air through an opening in said radial portion of the shield elements.
Claims (15)
- An apparatus for controlled delivery of cooling air to turbine blades (5) in a gas turbine (1) including a rotor unit (4), at least a first plurality of turbine blades (5) disposed in a first circumferential row (6; 7) around the rotor unit (4) and secured thereto, at least a second plurality of turbine blades (5) disposed in a second circumferential row (7; 8) around the rotor unit (4) and secured thereto, the first row (6; 7) and the second row (7; 8) being axially spaced with respect to one another, the apparatus including:- a plurality of rotor heat shield elements (23) disposed in a circumferential row between said first and second rows of turbine blades (5), each heat shield element (23) having a root portion (26) contoured so as to fit in a seat (27) of the rotor unit (4), an intermediate radial portion (28) and a shroud band (29) configured to be axially interposed between the first and second rows (6, 7; 7, 8) of turbine blades (5), the rotor heat shield elements (23) configured to define with said rotor unit (4) a rotor heat shield passage (33, 34, 35, 36) that is fed with cooling air;- a plurality of lock plates (40, 41, 42, 43) disposed in a circumferential row and configured to secure axially at least one of said first and second rows (6, 7, 8) of turbine blades (5) to said rotor unit (4), said lock plates (41, 42, 43) facing said heat shield elements (23),- a first cavity (33) between by the first row (6) of turbine blades (5) and the radial portion (28) of the shield elements (23) and a second cavity (34) between the radial portion (28) of the shield elements (23) and the second row (7) of turbine blades (5),at least one of said radial portion (28) of the rotor shield elements (23) and the lock plates (41, 42, 43) including at least one opening (48, 49; 54) for controlled flow of cooling air,
characterized in that one of said first and second cavity (33) is supplied by a source of cooling air, the other of said first and second cavity (34) being supplied with cooling air through the opening (48) in said radial portion (28) of the shield elements (23). - An apparatus as claimed in claim 1, characterized in that said rotor shield elements (23) include at least one feature (60) configured to cooperate with an axial finger (50) extending from the blades (5) of at least one row (6, 7, 8) in order to lock said rotor shield elements (23) circumferentially.
- An apparatus as claimed in claim 2, characterized in that said lock plates (42) include an opening (49) facing said features of said rotor shield elements (23), said opening (49) being configured to receive said finger (50) of a respective blade (5).
- An apparatus as claimed in any of the preceding claims, characterized in that the lock plates (42) are provided with hooks (51) for coupling with said rotor unit (4) .
- An apparatus as claimed in any preceding claims, characterized by including a circumferential wire seal between the root portions (26) of the said rotor heat shield elements (23) and said rotor unit (4).
- An apparatus as claimed in any preceding claims, characterized by including a circumferential wire seal between said lock plates (41, 42) and said rotor unit (4).
- An apparatus as claimed in any preceding claims, characterized by including circumferential seals (30) between said shroud bands (29) and said blades (5), and axial seals between each pair of adjacent shroud bands (29).
- A gas turbine including:- a rotor unit (4);- at least a first plurality of turbine blades (5) disposed in a first circumferential row (6, 7) around the rotor unit (4) and secured thereto,- at least a second plurality of turbine blades (5) disposed in a second circumferential row (7, 8) around the rotor unit (4) and secured thereto,- the first row and the second row (6, 7; 7, 8) being axially spaced with respect to one another, and- an apparatus for controlled delivery of cooling air to turbine blades (5) as claimed in any of the preceding claims.
- A gas turbine as claimed in claim 8, characterized in that said lock plates (42) include an opening (49) for controlled flow of cooling air between at least a first portion of said heat shield passage upstream of the lock plates (42) and a second portion of said heat shield passage downstream of the lock plates (42).
- A gas turbine as claimed in claim 9, characterized in that the blades (5) of at least one of said first and second rows (6, 7; 7, 8) have axial fingers (50), the rotor heath elements (23) having mating features (60) cooperating with said axial fingers (50) to lock said rotor shield elements (23) circumferentially, said axial fingers (50) of said blades (5) extending through said openings (49) of said locking plates (42).
- A gas turbine as claimed in claim 9 or 10, characterized in that said lock plates (42) include hooks (51) engaging corresponding seats in the rotor unit (4).
- A gas turbine as claimed in any of claims 9 to 11, characterized in that at least one of said first and second rows (6, 7; 7, 8) of blades (5) have platform portions (17) extending radially outwardly of said shroud bands (29) of the rotor heat shield elements (23).
- A gas turbine as claimed in claim 12, characterized in that said platform portions (17) include shiplap seal features configured to cooperate with corresponding features (55) of an adjacent blade (5).
- A gas turbine as claimed in any of claims 9 to 13, characterized in that the radial portions (28) of the rotor shield elements (23) include at least one opening (48) for controlled flow of cooling air.
- A gas turbine as claimed in any of claims 9 to 14, characterized in that shroud bands (29) have a plurality of inclined sealing fins (31) to cooperate at a short radial distance with a stepped inner sealing contour (32) of an inner ring (14) of the stator.
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP17205756.4A EP3495611B1 (en) | 2017-12-06 | 2017-12-06 | Apparatus for controlled delivery of cooling air to turbine blades in a gas turbine |
CN201811488034.4A CN110017175B (en) | 2017-12-06 | 2018-12-06 | Apparatus for controlled delivery of cooling air to turbine blades in a gas turbine |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP17205756.4A EP3495611B1 (en) | 2017-12-06 | 2017-12-06 | Apparatus for controlled delivery of cooling air to turbine blades in a gas turbine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP3495611A1 EP3495611A1 (en) | 2019-06-12 |
EP3495611B1 true EP3495611B1 (en) | 2020-07-29 |
Family
ID=60627499
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP17205756.4A Active EP3495611B1 (en) | 2017-12-06 | 2017-12-06 | Apparatus for controlled delivery of cooling air to turbine blades in a gas turbine |
Country Status (2)
Country | Link |
---|---|
EP (1) | EP3495611B1 (en) |
CN (1) | CN110017175B (en) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3120894B1 (en) * | 2021-03-19 | 2023-02-24 | Safran Aircraft Engines | TURBOMACHINE ROTOR, INCLUDING A LABYRINTH SEAL RING MOUNTED ON DISC FERRULES |
Family Cites Families (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB988541A (en) * | 1962-03-06 | 1965-04-07 | Ruston & Hornsby Ltd | Gas turbine rotor cooling |
US4884950A (en) * | 1988-09-06 | 1989-12-05 | United Technologies Corporation | Segmented interstage seal assembly |
FR2744761B1 (en) * | 1996-02-08 | 1998-03-13 | Snecma | LABYRINTH DISC WITH INCORPORATED STIFFENER FOR TURBOMACHINE ROTOR |
EP1917420A1 (en) | 2005-08-23 | 2008-05-07 | ALSTOM Technology Ltd | Device for securing installation of and fixing a heat shield element for a rotor unit of a flow engine |
US8388309B2 (en) * | 2008-09-25 | 2013-03-05 | Siemens Energy, Inc. | Gas turbine sealing apparatus |
DE102015111750A1 (en) * | 2015-07-20 | 2017-01-26 | Rolls-Royce Deutschland Ltd & Co Kg | Chilled turbine runner for an aircraft engine |
DE102016208759A1 (en) * | 2016-05-20 | 2017-11-23 | Siemens Aktiengesellschaft | Rotor disc with front-side sealing element |
-
2017
- 2017-12-06 EP EP17205756.4A patent/EP3495611B1/en active Active
-
2018
- 2018-12-06 CN CN201811488034.4A patent/CN110017175B/en active Active
Non-Patent Citations (1)
Title |
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None * |
Also Published As
Publication number | Publication date |
---|---|
CN110017175B (en) | 2023-08-04 |
CN110017175A (en) | 2019-07-16 |
EP3495611A1 (en) | 2019-06-12 |
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