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EP2543851A1 - Moteur à turbine à gaz - Google Patents

Moteur à turbine à gaz Download PDF

Info

Publication number
EP2543851A1
EP2543851A1 EP11750330A EP11750330A EP2543851A1 EP 2543851 A1 EP2543851 A1 EP 2543851A1 EP 11750330 A EP11750330 A EP 11750330A EP 11750330 A EP11750330 A EP 11750330A EP 2543851 A1 EP2543851 A1 EP 2543851A1
Authority
EP
European Patent Office
Prior art keywords
rotor
gas turbine
turbine engine
pipe unit
compressor
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.)
Withdrawn
Application number
EP11750330A
Other languages
German (de)
English (en)
Other versions
EP2543851A4 (fr
Inventor
Tomoki Taniguchi
Ryozo Tanaka
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.)
Kawasaki Heavy Industries Ltd
Kawasaki Motors Ltd
Original Assignee
Kawasaki Heavy Industries Ltd
Kawasaki Jukogyo KK
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 Kawasaki Heavy Industries Ltd, Kawasaki Jukogyo KK filed Critical Kawasaki Heavy Industries Ltd
Publication of EP2543851A1 publication Critical patent/EP2543851A1/fr
Publication of EP2543851A4 publication Critical patent/EP2543851A4/fr
Withdrawn legal-status Critical Current

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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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/085—Heating, heat-insulating or cooling means cooling fluid circulating inside the rotor

Definitions

  • the present invention relates to a gas turbine engine including a pipe for use as a passage of a cooling medium, a cable layout member, or the like.
  • Patent Literature 1 Japanese Laid-Open Patent Application Publication No. Hei. 11-257012
  • a compressor rotor or a turbine rotor in a gas turbine engine is assembled in such a manner that a plurality of rotor segments are coupled together in a center axis direction thereof. Therefore, it is difficult to form a pipe in an inner space of the rotor integrally with the rotor and fasten the pipe to the rotor by means of a fastener member such as a bolt, in terms of productivity. Therefore, it is necessary to insert the pipe into a through-hole provided inside of the rotor before or after assembling of the rotor. In this case, however, a small gap is unavoidably formed between the pipe and a peripheral wall of the through-hole. As a result, when the rotor is rotating at a high speed, the pipe whirls inside the through-hole, which causes a problem that efficiency and life of the gas turbine engine are reduced.
  • the present invention is directed to solving the above mentioned problem, and an object of the present invention is to provide a gas turbine engine which can prevent whirl of a pipe provided in an inner space of a rotor to transport a cooling medium or lay out cables, for example, and thus can achieve higher performance and reliability.
  • a gas turbine engine of the present invention comprises a hollow rotor including a plurality of rotor segments coupled together in a direction of its center axis and defining at least one of a compressor and a turbine; and a pipe unit inserted into an inner space of the rotor in the center axis direction, wherein a weight distribution of the pipe unit within an axial transverse section is eccentric with respect to the center axis of the rotor.
  • the pipe unit is provided in the inner space of the hollow rotor and is utilized as a cooling medium passage or a cable layout member, higher performance and higher functionality of the gas turbine engine can be achieved, while suppressing an increase in a dimension of the overall gas turbine engine. Since the weight distribution of the pipe unit is made eccentric, the pipe unit is displaced only in a specified direction with respect to the rotor, during rotation of the rotor. This makes it possible to suppress the pipe unit from whirling inside of the rotor. Therefore, reliability of the gas turbine engine can be maintained.
  • the pipe unit includes a pipe member and a flange provided on an outer periphery of the pipe member and fitted to an inner peripheral surface of the rotor.
  • a weight distribution of the flange within the axial transverse section is eccentric with respect to the center axis of the rotor. Since the flange is provided on the outer periphery of the pipe member, it becomes easy to mount the pipe unit to the rotor and position the pipe unit with respect to the rotor. Moreover, since the weight distribution of the flange within the axial transverse section is made eccentric, the pipe unit which is eccentric can be manufactured easily.
  • the pipe unit may constitute a passage of a cooling medium for cooling an interior of the gas turbine engine or a passage of seal air for sealing a bearing supporting the rotor such that the rotor is rotatable.
  • a cooling medium for cooling an interior of the gas turbine engine
  • a passage of seal air for sealing a bearing supporting the rotor such that the rotor is rotatable.
  • the pipe unit constitutes the cooling medium passage, or the seal air passage
  • the rotor may be a compressor rotor
  • the cooling medium or the seal air may be compressed air extracted from the compressor.
  • a cable may be extended to inside of the pipe unit.
  • a wire used to transmit a measurement signal of a temperature sensor, a strain sensor, etc. to inside of the pipe unit, as the cable, higher functionality of the gas turbine engine can be achieved by utilizing the inner space of the rotor.
  • Fig. 1 shows a gas turbine engine (hereinafter simply referred to as gas turbine) according to Embodiment 1 of the present invention.
  • a gas turbine 1 is configured such that a compressor 3 compresses air IA introduced from outside and guides the compressed air to a combustor 5, a fuel F is injected to the interior of the combustor 5 and combusted therein, and the resulting high-temperature and high-pressure combustion gas G drives a turbine 7.
  • a compressor side of the gas turbine 1 in a center axis direction will be referred to as "front side” and a turbine side of the gas turbine 1 in the center axis direction is referred to as "rear side.”
  • the compressor 3 is of an axial-flow type.
  • the axial-flow compressor 3 includes a compressor rotor 11 constituting the front portion of a rotary section of the gas turbine 1.
  • the compressor rotor 11 is divided into two sections, i.e., front and rear sections.
  • the compressor rotor 11 includes a compressor rotor body 11A which is the front section, and a compressor rotor extending section 11B coupled to the rear end portion of the compressor rotor body 11A by means of a bolt (not shown) such that the compressor rotor extending section 11B is unable to rotate relative to the compressor rotor body 11A.
  • a number of rotor vanes 13 are arranged on the outer peripheral surface of the compressor rotor body 11A.
  • the air IA suctioned from an air-intake tube 19 through a space between the housing 15 and an inner cowling 20 located radially inward relative to the housing 15 is compressed.
  • the compressed air CA is supplied to the combustor 5 via a diffuser 21 disposed downstream of the compressor 3.
  • the compressor rotor 11 includes a plurality of compressor rotor segments 23 stacked together and coupled together in a center axis direction of the compressor rotor 11.
  • Each compressor rotor segment 23 includes a disc 25 forming a radially inward portion.
  • the plurality of rotor vanes 13 are implanted on the outer peripheral portion of the disc 25 at equal intervals in a circumferential direction.
  • the compressor rotor 11 has a hollow shape.
  • Each compressor rotor segment 23 has a through-hole 27 penetrating the center portion of the disc 25 in the center axis direction.
  • the compressor rotor 11 entirely has a hollow portion 29 defined by the through-holes 27.
  • a plurality of combustors 5 are arranged at equal intervals in the circumferential direction of the gas turbine 1.
  • the compressed air CA supplied from the compressor 3 is mixed with the fuel F injected to the interior of the combustor 5 and combusted therein, and the resulting high-temperature and high-pressure combustion gas G flows into the turbine 7 through a turbine nozzle (first stator vane) 23.
  • the turbine 7 includes a turbine rotor 33 constituting the rear portion of the rotary section of the gas turbine 1 and a turbine casing 35 covering the turbine rotor 33.
  • a plurality of turbine stator vanes 37 are attached on the inner peripheral portion of the turbine casing 35 at predetermined intervals.
  • the turbine rotor 33 is provided with a plurality of turbine rotor vanes 39 positioned downstream of the turbine stator vanes 37, respectively.
  • the two rotors 11, 33 are entirely rotatably supported on the housing 15 via a front bearing 43, a center bearing 45, and a rear bearing 47.
  • a pipe unit 51 is inserted into the hollow portion 29 of the compressor rotor 11 in a direction of a rotor center axis C.
  • the pipe unit 51 includes a plurality of steel-made pipe members 53 having an outer diameter smaller than a hole diameter of the through-hole 27 and a plurality of steel-made flanges 55 provided on the outer peripheries of the pipe members 53.
  • the pipe unit 51 is inserted into the hollow portion 29 of the compressor rotor 11 from forward.
  • a front end portion 51a of the pipe unit 51 is fastened to the compressor rotor 11 via a disc-shaped support member 56 positioned at a front end portion 11a of the compressor rotor 11.
  • the plurality of pipe members 53 are arranged in series along the rotor center axis C. Adjacent pipe members 53 are coupled together by a flange 55. More specifically, the flange 55 includes an inner peripheral wall 55a fitted to the outer peripheral portions of the end portions of the pipe members 53 facing each other, an outer peripheral wall 55b fitted to the inner peripheral surface 11b of the compressor rotor 11, and a coupling wall 55c coupling the peripheral walls 55a, 55b together.
  • the two pipe members 53 are welded to the inner peripheral wall 53a and thereby joined together.
  • a slight gap S is present between the outer peripheral wall 55b of the flange 55 and the inner peripheral surface 11b of the compressor rotor 11, a slight gap S is present to allow the flange 55 to be inserted into the through-hole 27.
  • a plurality of (six in the present embodiment) flanges 55 are provided at axially different locations, only one flange 55 may be provided.
  • the pipe unit 51 is configured to have an eccentric weight distribution within an axial transverse section perpendicular to the rotor center axis C (hereinafter referred to as "weight distribution"), the weight distribution being eccentric with respect to the rotor center axis C.
  • weight distribution within an axial transverse section perpendicular to the rotor center axis C
  • the weight distribution of the flange 55 is made eccentric with respect to the rotor center axis C.
  • a weight 57 is embedded in a portion of the coupling wall 55c of the flange 55 to allow the weight distribution to be eccentric.
  • a portion of the coupling wall 55c of the flange 55 may be cut out to provide an axial through-hole 59.
  • a thinned-wall portion 61 may be provided by thinning a portion of the coupling wall 55c of the flange 55.
  • the weight distribution of the pipe unit 51 may be made eccentric with a small amount.
  • the outer peripheral wall 55b of the flange 55 may be pressed against the inner peripheral surface 11b of the compressor rotor 11 by rotating the flange 55 integrally with the compressor rotor 11, in a range of a rotational speed which is no less than 60% of a rated rotational speed of the compressor rotor 11.
  • the pipe unit 51 is configured such that the flange 55 is provided on the outer periphery of the pipe member 53 as described above, it becomes easy to mount the pipe unit 51 to the rotor and position the pipe unit 51 with respect to the rotor. In addition, by making the weight distribution of the flange 55 eccentric, it becomes easy to manufacture the pipe unit 51 having an eccentric weight distribution.
  • the structure of the pipe unit 51 is not limited to the example of Fig. 1 including the pipe member 53 and the flange 55, so long as the pipe unit 51 has an inner space extending axially and its weight distribution is eccentric.
  • the flange 55 may be omitted, and the pipe unit 51 may consist of the pipe member 53.
  • the thickness of the inner peripheral wall 53a may be set asymmetric with respect to the rotor center axis C.
  • the weight distribution of the pipe unit 51 can be made eccentric.
  • the pipe unit 51 forms a passage (cooling medium passage) RP of a cooling medium RA for cooling the interior of the gas turbine 1.
  • the pipe unit 51 extends from the front end portion 11a of the compressor rotor 11 to the rear end portion 11c of the compressor rotor 11.
  • the front end portion 51a of the pipe unit 51 penetrates a support member 56 and communicates with a compressed air extraction passage 63.
  • the rear end portion 51b of the pipe unit 51 opens toward the turbine rotor 33.
  • the compressed air CA extracted from the compressor 3 via the compressed air extraction passage 63 is guided to a region in the vicinity of the turbine rotor 33 through the cooling medium passage RP inside of the pipe member 53 and cools the turbine rotor 33 as the cooling medium RA.
  • the interior of the gas turbine can be cooled by utilizing the hollow portion 29 which is the inner space of the compressor rotor 11. Therefore, characteristics such as efficiency and life of the engine can be improved while suppressing an increase in a dimension of the gas turbine 1.
  • the compressed air CA extracted from the compressor 3 is used as the cooling medium RA, the cooling of the interior of the gas turbine 1 can be performed efficiently without introducing air for cooling.
  • the weight distribution of the pipe unit 51 is eccentric, the flange 55 of the pipe unit 51 is pressed against the inner peripheral surface 11b of the compressor rotor 11 by a centrifugal force in an eccentric direction P as shown in Fig. 3A , according to the rotation of the pipe unit 51 together with the compressor rotor 11. As a result, the pipe unit 51 is stably supported on the compressor rotor 11 and will not whirl.
  • Fig. 5 is a longitudinal sectional view showing the gas turbine engine 1 according to Embodiment 2 of the present invention.
  • the pipe unit 51 is formed as a passage SP of seal air for sealing the center bearing 45, rather than the cooling medium passage of Embodiment 1.
  • Embodiment 2 is identical to Embodiment 1 except for the following.
  • Fig. 6 is a longitudinal sectional view showing a region surrounding the center bearing 45, in an enlarged manner.
  • a bearing housing 65 which is a first bearing case is coupled to the downstream end portion of the inner peripheral wall of the diffuser 21, by means of a bolt which is not shown.
  • the bearing housing 65 covers an axial center portion of the compressor rotor extending section 11B at which the center bearing 45 is located.
  • a bearing box 67 which is a second bearing case is provided inward relative to the bearing housing 65.
  • a bearing chamber 60 is formed to accommodate the center bearing 45, radially inward relative to the bearing box 67.
  • Air seal mechanisms 69 are provided at both sides axially outward relative to the bearing chamber 60.
  • the air seal mechanism 69 is a seal mechanism for preventing high-temperature air LA which has leaked from the compressor 3 or high-temperature gas LG which has leaked from the combustor 5 from entering the bearing chamber 60 through a vent chamber 71 communicating with outside of the engine.
  • the vent chamber 71 is a space between the bearing housing 65 and the bearing box 67.
  • the compressor rotor extending section 11B is provided with through-holes extending from the hollow portion 29 to the air seal mechanisms 69, as seal air introduction passages 79 for providing communication between the center portion 29 and the air seal mechanisms 69.
  • a rear end portion 51b of the pipe member 53 of the pipe unit 51 is closed.
  • Air output holes 81 which are radial through-holes are provided on the peripheral wall of a portion of the compressor rotor extending section 11B which is inserted into the hollow portion 29.
  • the interior of the gas turbine can be sealed by utilizing the hollow portion 29 which is the inner space of the compressor rotor 11. Therefore, characteristics such as efficiency and life of the engine can be improved while suppressing an increase in a dimension of the gas turbine 1. Since the compressed air CA extracted from the compressor 3 is used as the seal air SA, the sealing of the interior of the gas turbine 1 can be performed efficiently without introducing air for cooling or sealing.
  • Fig. 7 is a cross-sectional view showing a gas turbine according to Embodiment 3 of the present invention.
  • a measurement cable 85 is extended to inside of the pipe unit 51.
  • Embodiment 3 is identical to Embodiment 1 except for the following.
  • the pipe unit 51 is extended from the front end portion 11a of the compressor rotor 11 to the rear end portion 11c of the compressor rotor 11.
  • the cable 85 is used to take out a measurement signal of a temperature of the turbine rotor 33 attached with rotor vanes of the turbine 7. Specifically, one end of the cable 85 is connected to a temperature sensor 87 attached on the turbine rotor 33, while the other end of the cable 85 is connected to a telemeter transmitter 89.
  • the telemeter transmitter 89 is a device for transmitting the measurement signal by radio.
  • Fig. 8 is an enlarged cross-sectional view showing a region surrounding the front end portion 11a of the compressor rotor 11 of Fig. 7 .
  • the telemeter transmitter 89 is mounted to an annular support 91 fastened to the front end portion 11a of the compressor rotor 11 together with the support member 56, by means of a bolt 90, and is rotatable with the compressor rotor 11.
  • the telemeter transmitter 89 has a transmission antenna 93 on its an inner peripheral portion.
  • a receiving antenna 95 of a telemeter receiver (not shown) is supported on an inner cowling 20 which is a non-rotating member of the compressor 3 and faces the transmission antenna 93 in a radial direction.
  • the measurement signal of the temperature sensor 87 of Fig. 7 is transmitted to the telemeter receiver installed outside via the cable 85, the transmission antenna 93 and the receiving antenna 95.
  • the sensor connected to one end of the cable 85 is the temperature sensor 87.
  • a measurement element connected to the cable 85 is not limited to the temperature sensor 87, but may be various measurement devices such as a strain sensor or a rotation sensor.
  • the cable 85 is not limited to the measurement cable 85 described in the present embodiment, but may be cables for various purposes as necessary such as control signal transmission or electric power transmission for a device installed inside. In this configuration, higher functionality and higher performance of the gas turbine engine can be achieved, by efficiently utilizing the hollow portion 29 which is the inner space of the compressor rotor 11.
  • the cable 85 inside the pipe unit 51 is not fastened to the interior of the pipe unit 51, it will whirl inside the pipe member 53 of the pipe unit 51, when it is rotating together with the compressor rotor 11 and the pipe unit 51.
  • the weight distribution of the pipe unit 51 within the axial transverse section is eccentric, it becomes possible to prevent the pipe unit 51 from whirling in the hollow portion 29 of the pipe unit 51 by the influence of the whirl of the cable 85.
  • the pipe unit 51 provided in the inner space of the rotor is utilized as a cable layout member, higher performance and higher functionality of the gas turbine 1 can be achieved, while suppressing an increase in the dimension of the overall gas turbine 1.
  • the pip unit 51 is provided in the hollow portion 29 of the compressor rotor 11, it may be provided in the turbine rotor 33 instead of or in addition to the compressor rotor 11.
  • the present invention is effective in achievement of higher performance and higher functionality of a gas turbine engine while suppressing an increase in a dimension of an overall gas turbine engine.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP11750330.0A 2010-03-01 2011-02-21 Moteur à turbine à gaz Withdrawn EP2543851A4 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP2010044426A JP4872006B2 (ja) 2010-03-01 2010-03-01 ガスタービンエンジン
PCT/JP2011/000945 WO2011108216A1 (fr) 2010-03-01 2011-02-21 Moteur à turbine à gaz

Publications (2)

Publication Number Publication Date
EP2543851A1 true EP2543851A1 (fr) 2013-01-09
EP2543851A4 EP2543851A4 (fr) 2013-11-06

Family

ID=44541886

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11750330.0A Withdrawn EP2543851A4 (fr) 2010-03-01 2011-02-21 Moteur à turbine à gaz

Country Status (5)

Country Link
US (1) US20130034451A1 (fr)
EP (1) EP2543851A4 (fr)
JP (1) JP4872006B2 (fr)
CA (1) CA2791191C (fr)
WO (1) WO2011108216A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3105438A4 (fr) * 2014-02-13 2017-10-04 United Technologies Corporation Collecteur de ventilation de nacelle
WO2017200644A1 (fr) * 2016-05-17 2017-11-23 General Electric Company Compresseur à gaz et procédé de refroidissement d'un élément rotatif
GB2574107A (en) * 2018-03-30 2019-11-27 Safran Aircraft Engines Assembly for a turbine engine
US11879411B2 (en) 2022-04-07 2024-01-23 General Electric Company System and method for mitigating bowed rotor in a gas turbine engine

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6094905A (en) * 1996-09-25 2000-08-01 Kabushiki Kaisha Toshiba Cooling apparatus for gas turbine moving blade and gas turbine equipped with same
EP1128158A2 (fr) * 2000-02-23 2001-08-29 General Electric Company Système de mesure pour déplacement de composante de rotor

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4571935A (en) * 1978-10-26 1986-02-25 Rice Ivan G Process for steam cooling a power turbine
FR2499652A1 (fr) * 1981-02-11 1982-08-13 Snecma Dispositif de correction de balourd de rotor de turbomachines
JP3334071B2 (ja) * 1997-05-16 2002-10-15 株式会社日立製作所 圧縮機ロータ
DE19757945B4 (de) * 1997-12-27 2006-11-30 Alstom Rotor für thermische Turbomaschine
JP3285816B2 (ja) * 1998-03-16 2002-05-27 三菱重工業株式会社 ガスタービンの冷却媒体移送パイプ
JP2003206701A (ja) * 2002-01-11 2003-07-25 Mitsubishi Heavy Ind Ltd ガスタービンのタービンローターおよびガスタービン
JP4113146B2 (ja) * 2004-03-17 2008-07-09 株式会社日立製作所 ガスタービン及びその遮熱管の外れ防止方法

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6094905A (en) * 1996-09-25 2000-08-01 Kabushiki Kaisha Toshiba Cooling apparatus for gas turbine moving blade and gas turbine equipped with same
EP1128158A2 (fr) * 2000-02-23 2001-08-29 General Electric Company Système de mesure pour déplacement de composante de rotor

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See also references of WO2011108216A1 *

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3105438A4 (fr) * 2014-02-13 2017-10-04 United Technologies Corporation Collecteur de ventilation de nacelle
US10443429B2 (en) 2014-02-13 2019-10-15 United Technologies Corporation Gas turbine nacelle ventilation manifold having a circumferential varying cross-sectional area
US10526910B2 (en) 2014-02-13 2020-01-07 United Technologies Corporation Gas turbine engine nacelle ventilation manifold for cooling accessories
WO2017200644A1 (fr) * 2016-05-17 2017-11-23 General Electric Company Compresseur à gaz et procédé de refroidissement d'un élément rotatif
US10337405B2 (en) 2016-05-17 2019-07-02 General Electric Company Method and system for bowed rotor start mitigation using rotor cooling
GB2574107A (en) * 2018-03-30 2019-11-27 Safran Aircraft Engines Assembly for a turbine engine
GB2574107B (en) * 2018-03-30 2022-09-21 Safran Aircraft Engines Assembly for a turbine engine
US11879411B2 (en) 2022-04-07 2024-01-23 General Electric Company System and method for mitigating bowed rotor in a gas turbine engine

Also Published As

Publication number Publication date
US20130034451A1 (en) 2013-02-07
CA2791191C (fr) 2014-08-05
CA2791191A1 (fr) 2011-09-09
JP2011179402A (ja) 2011-09-15
JP4872006B2 (ja) 2012-02-08
EP2543851A4 (fr) 2013-11-06
WO2011108216A1 (fr) 2011-09-09

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