CN101743380A - Turbine rotor blade - Google Patents

Turbine rotor blade Download PDF

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Publication number
CN101743380A
CN101743380A CN200980000565A CN200980000565A CN101743380A CN 101743380 A CN101743380 A CN 101743380A CN 200980000565 A CN200980000565 A CN 200980000565A CN 200980000565 A CN200980000565 A CN 200980000565A CN 101743380 A CN101743380 A CN 101743380A
Authority
CN
China
Prior art keywords
blade
turbine rotor
leaf
blade root
rule
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.)
Granted
Application number
CN200980000565A
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Chinese (zh)
Other versions
CN101743380B (en
Inventor
杼谷直人
檀野将平
山下匠生
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Mitsubishi Heavy Industries Ltd
Original Assignee
Mitsubishi Heavy Industries Ltd
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Mitsubishi Heavy Industries Ltd filed Critical Mitsubishi Heavy Industries Ltd
Publication of CN101743380A publication Critical patent/CN101743380A/en
Application granted granted Critical
Publication of CN101743380B publication Critical patent/CN101743380B/en
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • 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
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y10T29/49321—Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Even if the shape of a shroud of a turbine rotor blade in plan view is complicated, a blade root of the final (last) turbine rotor blade can be easily and quickly embedded into a blade groove of a turbine disc. A turbine rotor blade (1) comprising a blade root (3) which is embedded in a blade groove formed at the peripheral edge of a turbine disc and holds the entire blade, a blade portion (4) which is exposed to high-temperature gas, a platform (5) which supports the blade portion (4), a shank (6) which couples the blade root (3) and the platform (5), and a shroud (7) which extends along a circumferential direction from the end of the blade portion (4) includes a cutout portion (8) which is cut to a predetermined depth from the end of the blade root (3) to the midpoint of the shank (6) on the front edge side or rear edge side of the blade root (3) along the lengthwise direction thereof.

Description

Turbine rotor blade
Technical field
The present invention relates to a kind of turbine rotor blade that is applicable to gas turbine or steam turbine etc.
Background technique
As the turbine rotor blade that is applicable to gas turbine or steam turbine etc., the known blade root that has in the leaf groove of imbedding on the peripheral portion that is formed on the turbine disk and keep blade integral, the leaf portion that is exposed to high-temperature gas, the platform that supports this leaf portion, the petiole that links blade root and platform, scheme (for example with reference to patent documentation 1) from the front end of leaf portion along the guard shield of extending circumferentially.
Patent documentation 1: TOHKEMY 2006-283681 communique
But, in recent years, require further to reduce the leakage loss (gas leakage) of the front end of leaf portion, improve turbine efficiency, and require further to reduce the vibration of the front end of leaf portion, reduce the blade volume of leaf portion.Therefore, complex-shapedization during the overlooking of guard shield, as in the past with the blade root of turbine rotor blade in the buried one by one method in the leaf groove of the turbine disk, exist when finally the blade root of the turbine rotor blade of (at last) is imbedded in the leaf groove of the turbine disk, the final guard shield of the turbine rotor blade of (at last), interfere with the guard shield of the turbine rotor blade that is positioned at adjacent both sides, exist to be difficult to the blade root of the turbine rotor blade of final (at last) is imbedded problem in the leaf groove of the turbine disk.
In addition, also exist when the length (blade height) of turbine rotor blade for example under the situation for 200mm following short (low) (in more detail, L (blade height)/D (chord length) be under the situation 1/3 or more), the final blade root of the turbine rotor blade of (at last) can not be imbedded the problem in the leaf groove of the turbine disk.
Summary of the invention
The present invention researches and develops in view of the above problems, its purpose is to provide a kind of turbine rotor blade, even complex-shaped during the overlooking of the guard shield of turbine rotor blade, also can be easily and the blade root of turbine rotor blade that promptly will final (at last) be embedded in the leaf groove of the turbine disk.
The present invention in order to address the above problem, adopts following structure and method.
The turbine rotor blade of a mode of the present invention, have: imbed in the leaf groove on the peripheral portion that is formed on the turbine disk and keep the blade root of blade integral, the leaf portion that is exposed to high-temperature gas, the platform that supports this leaf portion, the petiole that links blade root and platform, guard shield from the front end of leaf portion along extending circumferentially, wherein, front edge side or the front end of trailing edge side along its length direction from described blade root that has described blade root cuts the extremely cut midway of described petiole with the degree of depth of regulation.
Turbine rotor blade according to an embodiment of the present invention, in the time of in blade root being imbedded the leaf groove that is assembled on the peripheral portion that is formed at the turbine disk, only, imbed between the rule blade and rule blade of prescribed depth (for example 5mm) and be arranged on respect to the leaf groove of the turbine disk by will in the plane of the end face that forms peripheral portion that comprises the turbine disk, moving (promptly from the radial direction outside towards the radial direction medial movement) by the end face that extends along its length that cut forms.
Even promptly complex-shaped during the overlooking of the guard shield of turbine rotor blade and rule blade (shape irrespectively when overlooking), make final (at last) at least imbed the turbine rotor blade of the blade employing present embodiment of the turbine disk then can be imbedded the blade root of the blade root of these turbine rotor blades and rule blade in the leaf groove of (bury to) turbine disk easily and promptly.
The turbine rotor of one embodiment of the present invention, owing to have when assembling on the leaf groove of blade root being imbedded on the peripheral portion that is formed on the turbine disk, can in the plane of the end face that forms peripheral portion that contains the turbine disk, move the turbine rotor blade of (promptly from the radial direction outside towards the radial direction medial movement) by the end face that extends along its length that cut forms, so can realize turbine rotor blade and rule blade are assembled in the simplification of the flow chart in the turbine disk, and can realize the shortening of the activity duration that assembling operation is required, thereby can realize the reduction of manufacture cost.
The manufacture method of the turbine rotor of above-mentioned mode of execution, at least a slice turbine rotor blade and multi-disc rule blade are imbedded in the turbine disk respectively, thereby finish turbine rotor, the described turbine rotor blade of a slice at least: have in the leaf groove of imbedding on the peripheral portion that is formed on the turbine disk and the blade root that keeps blade integral, be exposed to the leaf portion of high-temperature gas, support the platform of this leaf portion, the petiole that links blade root and platform, guard shield from the front end of leaf portion along extending circumferentially, front edge side or the front end of trailing edge side along its length direction from described blade root described blade root cut the extremely cut midway of described petiole with the degree of depth of regulation, described rule blade has: imbed in the leaf groove on the peripheral portion that is formed on the turbine disk and the blade root that keeps blade integral, be exposed to the leaf portion of high-temperature gas, support the platform of this leaf portion, the petiole that links blade root and platform, guard shield from the front end of leaf portion along extending circumferentially, wherein, have the stage as described below: with described turbine rotor blade from the radial direction outside towards the radial direction medial movement between the rule blade, this rule blade is meant that its blade root imbeds rule blade to prescribed depth with respect to the leaf groove of the described turbine disk, at described turbine rotor blade after between the rule blade, described turbine rotor blade and rule blade are moved on the axial direction of described turbine rotor, the blade root of described turbine rotor blade and rule blade is imbedded in the leaf groove of the described turbine disk.
Manufacture method according to the turbine rotor of above-mentioned mode of execution, in the time of in blade root being imbedded the leaf groove that is assembled on the peripheral portion that is formed at the turbine disk, only, imbed between the rule blade and rule blade of prescribed depth (for example 5mm) and be arranged on respect to the leaf groove of the turbine disk by will in the plane of the end face that forms peripheral portion that comprises the turbine disk, moving (promptly from the radial direction outside towards the radial direction medial movement) by the end face that extends along its length that cut forms.
Even promptly complex-shaped during the overlooking of the guard shield of turbine rotor blade and rule blade (shape irrespectively when overlooking), make final (at last) at least imbed the turbine rotor blade of the blade employing present embodiment of the turbine disk then can be imbedded the blade root of the blade root of these turbine rotor blades and rule blade in the leaf groove of (bury to) turbine disk easily and promptly.
Thus, can realize turbine rotor blade and rule blade are assembled in the simplification of the flow chart in the turbine disk, and can realize the shortening of the activity duration that assembling operation is required, can realize the reduction of manufacture cost.
According to turbine rotor blade of the present invention, though complex-shaped during the overlooking of guard shield that can play turbine rotor blade, also can be easily and the blade root of turbine rotor blade that promptly will final (at last) be embedded to effect in the leaf groove of the turbine disk.
Description of drawings
Figure 1A is the profile of the turbine rotor blade of expression one embodiment of the present invention.
Figure 1B is the plan view of the turbine rotor blade of expression one embodiment of the present invention.
Fig. 2 is the stereogram that the turbine rotor blade shown in Figure 1A and Figure 1B is observed from face side.
Fig. 3 A is the profile that expression does not have the rule blade of Figure 1A, Figure 1B and cut shown in Figure 2.
Fig. 3 B is the plan view that expression does not have the rule blade of Figure 1A, Figure 1B and cut shown in Figure 2.
Fig. 4 is the stereogram that the rule blade shown in presentation graphs 3A and Fig. 3 B is observed from face side.
Fig. 5 is the stereogram that is used to illustrate to the assembling sequence of the turbine disk.
Fig. 6 is the stereogram that is used to illustrate to the assembling sequence of the turbine disk.
Description of reference numerals
1 turbine rotor blade
2 turbine disks
2a leaf groove
3 blade roots
4 leaf portions
5 platforms
6 petioles
7 guard shields
8 cut
11 rule blades
13 blade roots
20 turbine rotors
Embodiment
Below, with reference to Figure 1A, Figure 1B and Fig. 2, a mode of execution of turbine rotor blade of the present invention is described.
Figure 1A is the profile of the turbine rotor blade of expression one embodiment of the present invention, and Figure 1B is the plan view of the turbine rotor blade of expression one embodiment of the present invention, and Fig. 2 is the stereogram that the related turbine rotor blade of present embodiment is observed from face side.
The turbine rotor blade 1 of present embodiment for example be applicable to have compression and combustion with the press part (not shown) of air, to the high-pressure air of sending here from this press part burner oil and make its burning, produce high-temperature combustion gas burning portion (not shown), be positioned at the downstream side of this burning portion, by the gas turbine of the turbine portion (not shown) of the combustion gases drive that flows out from burning portion.
As Figure 1A, Figure 1B and shown in Figure 2, turbine rotor blade 1 have among the leaf groove 2a (with reference to Fig. 5 and Fig. 6) that imbeds on the peripheral portion that is formed on the turbine disk 2 (with reference to Fig. 5 and Fig. 6) and keep (supporting) turbine rotor blade 1 integral body Xmas-tree blade root (foundation) 3, be exposed to leaf portion 4 in the high-temperature gas, support this leaf portion 4 platform 5, link the petiole 6 of blade root 3 and platform 5, from the front end (tip) of leaf portion 4 along extending circumferentially, prevent the guard shield 7 of leakage loss (gas leakage) of the front end of the resonance of turbine rotor blade 1 and reduction leaf portion 4.
In addition, the turbine rotor blade 1 of present embodiment, as Figure 1A and shown in Figure 2, has the cut 8 of cutting to similarly (with the degree of depth (for example 5mm) of regulation) of petiole 6 midway at the front edge side of blade root 3 or trailing edge side front end (lower end) along the length direction (being above-below direction among Figure 1A and Fig. 2) of turbine rotor blade 1 from blade root 3.The end face 8a that (among Figure 1A and the Fig. 2 for above-below direction) along its length that is formed by this cut 8 extends when being assembled on the turbine disk 2 at turbine rotor blade 1 with the peripheral portion that is formed on the turbine disk 2 on the mode of end face 2b almost parallel form, extend to petiole 6 midway.
Promptly, the cut 8 of turbine rotor blade 1, can imbed to the state of prescribed depth (for example 5mm) at the blade root 13 of Fig. 3 A, Fig. 3 B and turbine blade shown in Figure 4, that do not have cut 8 (below be called " rule blade ") 11 leaf groove 2a with respect to the turbine disk shown in Figure 52, to in the end face 8a that extends along its length that is formed by cut 8 is comprising the plane of the end face 2b that forms peripheral portion of the turbine disk 2, move, and simultaneously turbine rotor blade 1 is arranged between rule blade 11 and the rule blade 11 and form.
And, after turbine rotor blade 1 being arranged between rule blade 11 and the rule blade 11, as shown in Figure 6, make turbine blade 1 and rule blade 11 integral body along the moving axially of the turbine disk 2, blade root 3,13 integral body of turbine blade 1 and rule blade 11 are imbedded among the leaf groove 2a on the peripheral portion that is formed on the turbine disk 2.
In addition, the reference character 4,5,6,7 of Fig. 3 A, Fig. 3 B and Fig. 4 is respectively leaf portion, platform, leaf portion, guard shield, and its explanation is owing to using Figure 1A, Figure 1B and Fig. 2 to carry out explanation, so omit in this its explanation.
Reference character 20 expression of Fig. 5 and Fig. 6 has a slice turbine rotor blade 1, multi-disc rule blade 11 and the turbine disk 2 at least and the turbine rotor that constitutes.
In the turbine rotor blade 1 that constitutes like this, in the time of in blade root 3 being imbedded the leaf groove 2a that is assembled on the peripheral portion that is formed at the turbine disk 2, can be only by will in the plane of the end face 2b that forms peripheral portion that comprises the turbine disk 2, moving (promptly from the radial direction outside towards the radial direction medial movement) by the end face 8a that extends along its length that cut 8 forms, and the leaf groove 2a that is arranged on respect to the turbine disk 2 imbeds between the rule blade 11 and rule blade 11 of prescribed depth (for example 5mm).
Even promptly complex-shaped during the overlooking of the guard shield 7 of turbine rotor blade 1 and rule blade 11 (shape irrespectively when overlooking), make final (at last) at least imbed the turbine rotor blade 1 of the blade employing present embodiment of the turbine disk 2 then can be imbedded the blade root 13 of the blade root 3 of these turbine rotor blades 1 and rule blade 11 among the leaf groove 2a of (bury to) turbine disk 2 easily and promptly.
Turbine rotor 20 according to present embodiment, work as blade root 3 owing to have, when assembling on the 13 leaf groove 2a that imbed on the peripheral portion that is formed on the turbine disk 2, the end face 8a that go up to extend along its length that the cut 8 by turbine rotor blade 1 can be formed moves the turbine rotor blade 1 of (promptly from the radial direction outside towards the radial direction medial movement) in the plane of the end face 2b that forms peripheral portion that contains the turbine disk 2, so can realize turbine rotor blade 1 and rule blade 11 are assembled in the simplification of the flow chart in the turbine disk 2, and can realize the shortening of the activity duration that assembling operation is required, can realize the reduction of manufacture cost.
The present invention not only can be applicable to gas turbine, also can be applicable to steam turbine, other have the fluid rotary machine with spline structure.
The present invention is not limited to above-mentioned mode of execution, and in the scope that does not break away from technical conceive of the present invention, the distortion that can suit is as required implemented, change is implemented.

Claims (3)

1. turbine rotor blade, it has: imbed in the leaf groove on the peripheral portion that is formed on the turbine disk and keep the blade root of blade integral, the leaf portion that is exposed to high-temperature gas, the platform that supports this leaf portion, the petiole that links blade root and platform, the guard shield from the front end of leaf portion along extending circumferentially, it is characterized in that
Described turbine rotor blade has cut, this cut the front edge side of described blade root or the front end of trailing edge side along its length direction from described blade root with the degree of depth of regulation cut to described petiole midway.
2. turbine rotor is characterized in that having:
At least the described turbine rotor blade of a slice claim 1;
The multi-disc rule blade, this rule blade has: imbed in the leaf groove on the peripheral portion that is formed on the turbine disk and keep the blade root of blade integral, the leaf portion that is exposed to high-temperature gas, the platform that supports this leaf portion, the petiole that links blade root and platform, the guard shield from the front end of leaf portion along extending circumferentially;
The described turbine disk.
3. the manufacture method of a turbine rotor,
At least a slice turbine rotor blade and multi-disc rule blade are imbedded respectively in the turbine disk, thereby finish turbine rotor,
The described turbine rotor blade of a slice at least has: imbed in the leaf groove on the peripheral portion that is formed on the described turbine disk and keep the blade root of blade integral, the leaf portion that is exposed to high-temperature gas, the platform that supports this leaf portion, the petiole that links blade root and platform, the guard shield from the front end of leaf portion along extending circumferentially, cut cut midway to described petiole at the front edge side of described blade root or the front end of trailing edge side along its length direction from described blade root with the degree of depth of regulation
Described rule blade has: imbed in the leaf groove on the peripheral portion that is formed on the described turbine disk and keep the blade root of blade integral, the leaf portion that is exposed to high-temperature gas, the platform that supports this leaf portion, the petiole that links blade root and platform, the guard shield from the front end of leaf portion along extending circumferentially
The manufacture method of described turbine rotor is characterised in that,
Have the stage as described below: with described turbine rotor blade from the radial direction outside towards the radial direction medial movement between the rule blade, this rule blade is meant that its blade root imbeds rule blade to prescribed depth with respect to the leaf groove of the described turbine disk, after described turbine rotor blade is between rule blade, described turbine rotor blade and rule blade are moved on the axial direction of described turbine rotor, the blade root of described turbine rotor blade and rule blade is imbedded in the leaf groove of the described turbine disk.
CN200980000565.7A 2008-01-16 2009-01-08 Turbine rotor blade Expired - Fee Related CN101743380B (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
JP2008006895 2008-01-16
JP006895/2008 2008-01-16
PCT/JP2009/050160 WO2009090908A1 (en) 2008-01-16 2009-01-08 Turbine rotor blade

Publications (2)

Publication Number Publication Date
CN101743380A true CN101743380A (en) 2010-06-16
CN101743380B CN101743380B (en) 2014-01-01

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Application Number Title Priority Date Filing Date
CN200980000565.7A Expired - Fee Related CN101743380B (en) 2008-01-16 2009-01-08 Turbine rotor blade

Country Status (7)

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US (1) US20110217175A1 (en)
EP (1) EP2230385A4 (en)
JP (1) JP4939613B2 (en)
CN (1) CN101743380B (en)
RU (1) RU2010104753A (en)
WO (1) WO2009090908A1 (en)
ZA (1) ZA201001031B (en)

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EP2551460A1 (en) * 2011-07-29 2013-01-30 Siemens Aktiengesellschaft Blade group
US10309232B2 (en) * 2012-02-29 2019-06-04 United Technologies Corporation Gas turbine engine with stage dependent material selection for blades and disk
US10648354B2 (en) 2016-12-02 2020-05-12 Honeywell International Inc. Turbine wheels, turbine engines including the same, and methods of forming turbine wheels with improved seal plate sealing
US10704400B2 (en) * 2018-10-17 2020-07-07 Pratt & Whitney Canada Corp. Rotor assembly with rotor disc lip
KR20230081267A (en) * 2021-11-30 2023-06-07 두산에너빌리티 주식회사 Turbine blade, turbine and gas turbine including the same

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Also Published As

Publication number Publication date
CN101743380B (en) 2014-01-01
EP2230385A1 (en) 2010-09-22
EP2230385A4 (en) 2011-03-16
JPWO2009090908A1 (en) 2011-05-26
JP4939613B2 (en) 2012-05-30
ZA201001031B (en) 2011-08-31
RU2010104753A (en) 2012-02-27
US20110217175A1 (en) 2011-09-08
WO2009090908A1 (en) 2009-07-23

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