JP2002089202A - Back pressure turbine for driving barrel-type compressor - Google Patents
Back pressure turbine for driving barrel-type compressorInfo
- Publication number
- JP2002089202A JP2002089202A JP2000278223A JP2000278223A JP2002089202A JP 2002089202 A JP2002089202 A JP 2002089202A JP 2000278223 A JP2000278223 A JP 2000278223A JP 2000278223 A JP2000278223 A JP 2000278223A JP 2002089202 A JP2002089202 A JP 2002089202A
- Authority
- JP
- Japan
- Prior art keywords
- blades
- pressure turbine
- blade
- steam
- barrel
- 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- Withdrawn
Links
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
【０００１】[0001]
【発明の属する技術分野】本発明はバレル型圧縮機駆動
用背圧タービンに関し、翼の段数、枚数を減らし、翼の
ディスク強度も向上させると共にタービン全体を小型化
して高速回転にも適用可能としたものである。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a back pressure turbine for driving a barrel type compressor, and it is applicable to high speed rotation by reducing the number of blades and the number of blades, improving the disk strength of the blades, and reducing the size of the entire turbine. It was done.
【０００２】[0002]
【従来の技術】小型バレル型の圧縮機を駆動する背圧タ
ービンは中小型の蒸気タービンプラントに用いられてお
り、タービンの構造は、図示しないが、円筒状のケーシ
ング内に蒸気を導きラトー翼が設けられたロータを回転
させて圧縮機を駆動するものであり、その排気はプラン
ト内の他の蒸気系に導かれ、再利用されるものである。
ラトー翼は一般には、３段で構成され、動翼はディスク
周方向に７４枚が配置され、静翼はケーシング側内周面
に４８枚が配設されている。現状のバレル型背圧タービ
ンは、回転数が１５０００r.p.m 、出力は３０００ＫＷ
程度のものが実現されている。しかし、近年では更に高
速回転数のものが要求されるようになっており、回転数
が１８０００r.p.m で６０００ＫＷ級のものの開発が必
要となっている。このような高速回転の背圧タービンで
は、現状の構造では翼のディスク部の強度が不足し、更
に、高速回転数であるが故に軸振動が大きくなり、軸に
過大な曲げ応力が発生するので、高速回転数で運転でき
る小型のバレル型圧縮機駆動用の背圧タービンの開発が
望まれていた。2. Description of the Related Art A back-pressure turbine for driving a small-barrel type compressor is used in small and medium-sized steam turbine plants. The structure of the turbine is not shown, but the steam is introduced into a cylindrical casing to introduce a Latau blade. The compressor is driven by rotating the rotor provided with the exhaust gas, and the exhaust gas is guided to another steam system in the plant and reused.
Generally, a Lato blade is configured in three stages, 74 blades are arranged in the disk circumferential direction, and 48 stator blades are arranged on the inner peripheral surface on the casing side. The current barrel type back pressure turbine has a rotation speed of 15000 rpm and an output of 3000 KW
Some degree has been realized. However, in recent years, even higher rotation speeds have been required, and development of a rotation speed of 18,000 rpm and a 6000 KW class is required. In such a high-speed rotating back-pressure turbine, the current structure lacks the strength of the disk portion of the blade, and furthermore, because of the high-speed rotation, the shaft vibration increases and excessive bending stress is generated on the shaft. It has been desired to develop a compact back-pressure turbine for driving a barrel-type compressor that can be operated at a high rotational speed.
【０００３】[0003]
【発明が解決しようとする課題】前述のように圧縮機を
駆動する背圧タービンは、近年では１８０００r.p.m の
高速度のタービンが要求されるようになってきており、
このような高速回転数領域においては、翼の強度を向上
させる構造としなければならず、又、軸振動も大きくな
り、軸振動を低減させるような構造にしなければならな
い。そのためには背圧タービンの構造を現状のものより
は大幅に改良し小型で、かつ、高速度に耐え得る背圧タ
ービンの開発が望まれていた。As described above, as a back pressure turbine for driving a compressor as described above, a high-speed turbine of 18,000 rpm has recently been required.
In such a high-speed rotation region, the structure must be such that the strength of the blade is improved, and the shaft vibration must be increased to reduce the shaft vibration. To this end, there has been a demand for the development of a back pressure turbine that is significantly improved in structure of the back pressure turbine compared with the existing one, and that is small and can withstand high speeds.
【０００４】そこで本発明では、高速回転時に耐えるよ
うに翼のディスク強度を向上させると共に、翼の段数と
翼の枚数も減少させることにより、軸受スパンを短く
し、これによりタービン自体も小型化して振動も減少さ
せ、高速回転を可能とするバレル型圧縮機駆動用背圧タ
ービンを提供することを課題としてなされたものであ
る。Therefore, in the present invention, the bearing span is shortened by improving the disk strength of the blade so as to withstand high-speed rotation, and by reducing the number of blade stages and the number of blades, thereby reducing the size of the turbine itself. An object of the present invention is to provide a back-pressure turbine for driving a barrel-type compressor that also reduces vibration and enables high-speed rotation.
【０００５】[0005]
【課題を解決するための手段】本発明は前述の課題を解
決するために次の（１）〜（４）の手段を提供する。The present invention provides the following means (1) to (4) to solve the above-mentioned problems.
【０００６】（１）蒸気をバレル内へ導き静翼と動翼で
構成されるタービン部に流し回転軸を回転させて圧縮機
を駆動するバレル型圧縮機駆動用背圧タービンにおい
て、前記静翼及び動翼は２段で構成されると共に、回転
数は１５０００〜１８０００回転／分であることを特徴
とするバレル型圧縮機駆動用背圧タービン。(1) A back-pressure turbine for driving a barrel-type compressor in which steam is guided into a barrel, flows through a turbine section composed of stationary blades and moving blades, and rotates a rotating shaft to drive a compressor. A back pressure turbine for driving a barrel-type compressor, wherein the rotor blades are composed of two stages and the number of revolutions is 15,000 to 18,000 revolutions / minute.
【０００７】（２）前記動翼が取付けられるディスクの
軸中心線と直交する線分に対する傾斜角度は２０〜２２
度とし、ディスクの基本直径は４００mm以下としたこと
を特徴とする（１）記載のバレル型圧縮機駆動用背圧タ
ービン。(2) The inclination angle of the disk to which the rotor blade is attached with respect to a line perpendicular to the axial center line is 20 to 22.
The back pressure turbine for driving a barrel type compressor according to (1), wherein the basic diameter of the disk is 400 mm or less.
【０００８】（３）前記回転軸の軸受間のスパンは８０
０mm以下で、軸受スパンをＬとし回転軸の径をＤとして
Ｌ／Ｄを６．０未満とすることを特徴とする（１）記載
のバレル型圧縮機駆動用背圧タービン。(3) The span between the bearings of the rotary shaft is 80
(1) The back pressure turbine for driving a barrel type compressor according to (1), wherein L / D is less than 6.0, where L is the bearing span, L is the diameter of the rotating shaft, and D is the diameter of the rotating shaft.
【０００９】（４）蒸気をバレル内へ導き静翼と動翼で
構成されるタービン部に流し回転軸を回転させて圧縮機
を駆動するバレル型圧縮機駆動用背圧タービンにおい
て、前記静翼及び動翼は２段で構成されると共に、前記
回転軸の回転数は１５０００〜１８０００回転／分であ
り、軸受間のスパンは８００mm以下で、軸受スパンをＬ
とし回転軸の径をＤとしてＬ／Ｄを６．０未満に設定
し、更に前記動翼が取付けられるディスクの軸中心線と
直交する線分に対する傾斜角度は２０〜２２度とし、前
記動翼の基本直径は４００mm以下としたことを特徴とす
る（１）記載のバレル型圧縮機駆動用背圧タービン。(4) In a barrel type compressor back pressure turbine for driving a compressor by guiding steam into a barrel and flowing the steam into a turbine section comprising a stationary blade and a moving blade to rotate a rotating shaft and drive the compressor. And the rotor blades are configured in two stages, the number of rotations of the rotating shaft is 15,000 to 18,000 rpm, the span between bearings is 800 mm or less, and the bearing span is L.
L / D is set to less than 6.0, where D is the diameter of the rotating shaft, and the inclination angle with respect to a line perpendicular to the axis of the disk on which the moving blade is mounted is 20 to 22 degrees. The back pressure turbine for driving a barrel type compressor according to (1), wherein the basic diameter of the back pressure turbine is 400 mm or less.
【００１０】本発明の（１）のバレル型圧縮機駆動用背
圧タービンは、翼が２段構成であり、従来の３段構成よ
りも小さくしている。このような構造により、従来の背
圧タービンよりも軸受間のスパンを短くすることがで
き、軸振動特性を従来より向上させている。従って、動
翼取付部の強度向上と軸振動特性の向上により、現状の
１５０００r.p.m の回転数から従来対応ができなかった
１８０００r.p.m の高速回転の背圧タービンの開発が可
能となる。The back pressure turbine for driving a barrel type compressor of (1) of the present invention has a two-stage blade, which is smaller than a conventional three-stage blade. With such a structure, the span between the bearings can be made shorter than in the conventional back pressure turbine, and the shaft vibration characteristics are improved compared to the conventional case. Therefore, by improving the strength of the rotor blade mounting portion and the shaft vibration characteristics, it is possible to develop a high-speed back pressure turbine of 18,000 rpm which could not be conventionally supported from the current speed of 15,000 rpm.
【００１１】本発明の（２）の発明では、ディスクの傾
斜角度が従来の６〜１０度よりも大きくし、基本直径は
４００mmとして従来よりも小さく設定している。この結
果、ディスク部は厚肉構造となり、基本直径が短くなっ
た分遠心力の影響も小さくなり、振動特性が向上するも
のである。In the invention (2) of the present invention, the inclination angle of the disk is set to be larger than the conventional 6 to 10 degrees, and the basic diameter is set to be smaller than 400 mm. As a result, the disk portion has a thick structure, and the influence of the centrifugal force is reduced by the reduced basic diameter, thereby improving the vibration characteristics.
【００１２】本発明の（３）では、軸受スパンを従来よ
りも短くして８００mm以下とし、Ｌ／Ｄも従来の６．６
〜７．５の範囲から６．０未満として小さくしたので回
転軸の振動特性がより確実に向上し、高速回転が可能と
なるものである。In (3) of the present invention, the bearing span is made shorter than the conventional one to 800 mm or less, and the L / D is 6.6 of the conventional type.
The vibration characteristic of the rotating shaft is more reliably improved, and high-speed rotation is possible, since the range is reduced from the range of 7.5 to less than 6.0.
【００１３】本発明の（４）では、上記（１）〜（３）
の発明のすべての要件を備えたものであり、ディスク部
の強度向上と回転軸の強度及び振動特性が総合的に向上
し、１５０００〜１８０００回転／分の高速回転を可能
とするバレル型圧縮機駆動用背圧タービンが確実に実現
できるものである。In (4) of the present invention, the above (1) to (3)
A barrel-type compressor which has all the requirements of the invention of the present invention, improves the strength of the disk portion, improves the strength and vibration characteristics of the rotating shaft comprehensively, and enables high-speed rotation of 15,000 to 18000 rpm. A driving back-pressure turbine can be reliably realized.
【００１４】[0014]
【発明の実施の形態】以下、本発明の実施の形態につい
て図面に基づいて具体的に説明する。図１は本発明の実
施の一形態に係るバレル型圧縮機駆動用背圧タービンの
断面図であるり、本発明の背圧タービンは１５０００〜
１８０００r.p.m で高速回転するものである。図におい
て、１０は背圧タービンケーシングであり、１１は回転
軸である。１２は圧縮機側のラジアル荷重を受けるジャ
ーナル軸受、１３は反対側のジャーナル軸受で、両軸受
１３，１４間のスパンは従来の８００mm〜９００mmから
７３０mm〜８００mmと短くし、振動特性を向上するよう
にしている。１４は同じ側のスラスト軸受でアキシャル
荷重を受けるものである。Embodiments of the present invention will be specifically described below with reference to the drawings. FIG. 1 is a sectional view of a back-pressure turbine for driving a barrel-type compressor according to an embodiment of the present invention.
It rotates at a high speed of 18000 rpm. In the figure, reference numeral 10 denotes a back pressure turbine casing, and 11 denotes a rotating shaft. Numeral 12 is a journal bearing which receives a radial load on the compressor side, and numeral 13 is a journal bearing on the opposite side. I have to. Numeral 14 denotes an axial load on the thrust bearing on the same side.
【００１５】１５は１段静翼、１６は１段動翼、１７は
２段静翼、１８は２段動翼である。これら翼は従来は３
段構成であったが、本発明では２段構成であり、又、翼
の周方向の枚数も静翼が従来の４８枚から３４枚へ、動
翼が従来の７４枚から６２枚へと減少させている。２０
は回転軸の１段動翼１６が取り付けられるディスク部で
あり、２１は２段動翼が取り付けられるディスク部であ
り、後述するように強度を補強するように厚みを増加さ
せている。又、軸受スパンをＬ、回転軸の径をＤとして
Ｌ／Ｄを従来の６．６〜７．５から５．２〜５．７に変
更し、振動を少なくする構造としている。Reference numeral 15 denotes a one-stage stationary blade, 16 denotes a one-stage moving blade, 17 denotes a two-stage stationary blade, and 18 denotes a two-stage moving blade. These wings are conventionally 3
In the present invention, the number of blades in the circumferential direction is reduced from 48 to 34, and the number of moving blades is reduced from 74 to 62 in the present invention. Let me. 20
Numeral denotes a disk portion to which the first-stage moving blade 16 of the rotating shaft is attached, and 21 denotes a disk portion to which the two-stage moving blade is attached. The thickness is increased so as to reinforce the strength as described later. Also, the bearing span is L and the diameter of the rotating shaft is D, and L / D is changed from 6.6 to 7.5 to 5.2 to 5.7 to reduce vibration.
【００１６】２２，２３はシール部であり、回転軸１１
とケーシング１０との隙間を、それぞれ両側の軸貫通部
において蒸気の流出を防止するようにシールしている。
２４は蒸気入口であり、図示していない入口管より蒸気
が流入する。２５はノズル部であり、蒸気入口より高圧
の蒸気をタービン部通路内へ噴出させるものである。２
６は蒸気通路であり、１段〜２段の各翼１５，１６，１
７，１８を通過し、膨張することにより回転軸１１に回
転エネルギーを与えて低圧となった蒸気が流れる。２７
は蒸気出口であり、仕事を終えた低圧蒸気が通路２６か
ら流出する。２８，２９は潤滑油の供給口、３０は潤滑
油の出口である。Reference numerals 22 and 23 denote sealing portions,
The gap between the casing and the casing 10 is sealed so as to prevent the outflow of steam at the shaft penetration portions on both sides.
Reference numeral 24 denotes a steam inlet through which steam flows from an inlet pipe (not shown). Numeral 25 denotes a nozzle for discharging high-pressure steam from the steam inlet into the turbine passage. 2
Reference numeral 6 denotes a steam passage, each of the blades 15, 16, 1 of one or two stages.
The steam that has passed through 7 and 18 and expanded to give rotational energy to the rotating shaft 11 to be reduced in pressure flows. 27
Is a steam outlet, and the low-pressure steam that has finished its work flows out of the passage 26. 28 and 29 are lubricating oil supply ports, and 30 is a lubricating oil outlet.
【００１７】上記構成のバレル型圧縮機駆動用背圧ター
ビンにおいて、蒸気入口２４よりケーシング内に流入す
る蒸気４０はノズル部２５からタービン部の通路へ噴出
し、１段静翼１５、１段動翼１６、２段静翼１７、２段
動翼１８を通過する過程において膨張することにより回
転軸１１に回転エネルギーを与え、蒸気通路２６へ４０
ａで示すように流出し、蒸気出口２７から４０ｂで示す
ように流出する。回転エネルギーを与えられた回転軸１
１は図中左側にある（図示していない）圧縮機へ連結さ
れており、これを回転させる。In the barrel type back pressure turbine for driving a compressor of the above construction, the steam 40 flowing into the casing from the steam inlet 24 is ejected from the nozzle portion 25 to the passage of the turbine portion, the first stage stationary blade 15 and the one stage blade 16. By expanding in the process of passing through the two-stage stationary blade 17 and the two-stage moving blade 18, rotation energy is given to the rotating shaft 11,
It flows out as shown by a, and flows out from the steam outlet 27 as shown by 40b. Rotary shaft 1 given rotational energy
1 is connected to a compressor (not shown) on the left side of the figure and rotates it.
【００１８】図２は図１に示す１段，２段動翼を代表し
て示した図である。図において動翼１６，１８は回転軸
１１のディスク部２０，２１に、それぞれ取り付けられ
ており、ディスク部２０，２１は回転軸１１の中心線４
０に直交する線分に対してθの角度を有したテーパ形状
であり、従来のθは、６度から１０度の範囲であったが
本発明では、θ≧２０度、好ましくは２０〜２２度とし
てディスク部の軸側への広がりを大きくし、ディスク部
を厚肉構造として強度を向上させている。又、基本直径
（ＬＲ×２）は従来の４０８mmから３５６mmとして小さ
くし、遠心力の影響を小さくしている。FIG. 2 is a view representatively showing the one-stage and two-stage blades shown in FIG. In the figure, rotor blades 16 and 18 are respectively attached to disk portions 20 and 21 of rotating shaft 11, and disk portions 20 and 21 are attached to center line 4 of rotating shaft 11.
It is a tapered shape having an angle of θ with respect to a line segment orthogonal to 0, and the conventional θ is in the range of 6 degrees to 10 degrees, but in the present invention, θ ≧ 20 degrees, preferably 20 to 22 degrees. The degree of expansion of the disk portion toward the axial side is increased, and the disk portion has a thick structure to improve strength. The basic diameter (LR × 2) is reduced to 356 mm from the conventional 408 mm to reduce the influence of the centrifugal force.
【００１９】図３は翼の形状及び配置を示す図で、
（ａ）は静翼、（ｂ）は動翼を、それぞれ示している。
図中、実線は本発明の翼、点線は従来の翼をそれぞれ示
している。図３（ａ）において本発明の静翼１５，１７
の翼幅は、Ｄ1 ＝３０mmとし、従来の翼幅Ｄ2 ＝２５mm
よりも大きくしている。又、本発明の翼の配列の平均ピ
ッチＰＳ1 ＝３５，８９mmとし、従来のピッチＰＳ2 ＝
２５，４３mmよりも大きくしている。又、（ｂ）におい
て、本発明の動翼１６，１８の平均ピッチＰＭ1 ＝１
９，７９mmとし、従来のピッチＰＭ2 ＝１６，５９mmよ
りも大きくしている。従って、翼枚数は、静翼では従来
４８枚あったものを３４枚と少なくし、動翼では、従来
７４枚あったものを６２枚と少なくしている。FIG. 3 is a view showing the shape and arrangement of the wing.
(A) shows a stationary blade and (b) shows a moving blade.
In the figure, the solid line shows the blade of the present invention, and the dotted line shows the conventional blade. In FIG. 3A, the stationary blades 15 and 17 of the present invention are shown.
The wing width, and D 1 = 30 mm, conventional wingspan D 2 = 25 mm
Larger than. The average pitch PS 1 of the wing arrangement of the present invention is 35,89 mm, and the conventional pitch PS 2 =
It is larger than 25 and 43 mm. In (b), the average pitch PM 1 = 1 of the blades 16 and 18 of the present invention.
The pitch is 9,79 mm, which is larger than the conventional pitch PM 2 = 16,59 mm. Accordingly, the number of blades is reduced from 34 for stationary vanes to 34 for conventional blades, and reduced to 62 from 74 for stationary blades.
【００２０】上記に説明の本発明の実施の形態において
は、翼の構成を２段としたので、従来の３段構成よりも
回転軸１１の長さを短くすることができ、ジャーナル軸
受１２，１３間のスパンが小さくなり、その結果、軸の
撓み量が小さくなり、曲げ応力の発生や振動の発生も少
なく抑えることが可能となる。In the embodiment of the present invention described above, the blades are configured in two stages, so that the length of the rotating shaft 11 can be made shorter than in the conventional three-stage configuration, and the journal bearings 12 and 13 is reduced, and as a result, the amount of bending of the shaft is reduced, and the occurrence of bending stress and vibration can be suppressed.
【００２１】又、動翼１６，１８のディスク部２０，２
１のテーパ形状も傾斜角度を従来の１０度程度のものを
２０度以上としたのでディスク部２０，２１の回転軸１
１への付根部の肉厚が厚くなり、高速回転時の強度、剛
性が増して振動も減少させることができる。更に静翼１
５，１７の枚数も従来の４８から３４枚へ減少させ、か
つ、翼幅も大きくし、又、動翼の枚数も従来の７４枚か
ら６２枚へ減少させたので、高速回転時の翼の振動の影
響も少なくなり、蒸気流量も増加させてタービン効率を
向上させることが可能となる。更に、上記の段数の減
少、静翼、動翼の枚数の減少により背圧タービン全体の
小型化が可能になり、低コスト化も可能となる。Also, the disk portions 20, 2 of the rotor blades 16, 18
Since the taper shape of the disk unit 1 has a tilt angle of about 10 degrees in the related art and 20 degrees or more, the rotation axis
The thickness of the base at the base 1 is increased, and the strength and rigidity at the time of high-speed rotation are increased, and vibration can be reduced. Furthermore, stationary blade 1
The number of blades 5 and 17 was also reduced from the conventional 48 to 34, the blade width was increased, and the number of rotor blades was also reduced from the conventional 74 to 62. The influence of the vibration is reduced, and the steam flow rate is increased, so that the turbine efficiency can be improved. Furthermore, the reduction in the number of stages and the number of stationary blades and moving blades allow the whole back pressure turbine to be reduced in size and cost.
【００２２】[0022]
【発明の効果】本発明のバレル型圧縮機駆動用背圧ター
ビンは、蒸気をバレル内へ導き静翼と動翼で構成される
タービン部に流し回転軸を回転させて圧縮機を駆動する
バレル型圧縮機駆動用背圧タービンにおいて、前記静翼
及び動翼は２段で構成されると共に、回転数は１５００
０〜１８０００回転／分であることを特徴としている。The barrel type back pressure turbine for driving a compressor according to the present invention drives a compressor by guiding steam into the barrel and flowing the steam through a turbine section composed of stationary blades and moving blades to rotate a rotating shaft. In the back-pressure turbine for driving the compressor, the stationary blade and the moving blade are configured in two stages, and the rotation speed is 1500.
It is characterized by a speed of 0 to 18000 revolutions / minute.
【００２３】上記の構成により、従来の背圧タービンよ
りも軸受間のスパンを短くすることができ、軸振動特性
を従来より向上させている。従って、動翼取付部の強度
向上と軸振動特性の向上により、現状の１５０００r.p.
m の回転数から従来対応ができなかった１８０００r.p.
m の高速回転の背圧タービンの開発が可能となる。With the above configuration, the span between the bearings can be made shorter than in the conventional back pressure turbine, and the shaft vibration characteristics are improved as compared with the conventional case. Therefore, by improving the strength of the rotor blade mounting part and the shaft vibration characteristics, the current 15000 r.p.
18000r.p.
m high-speed rotating back-pressure turbine can be developed.
【００２４】本発明の（２）の発明では、ディスクの傾
斜角度が従来の６〜１０度よりも大きくし、基本直径は
４００mmとして従来よりも小さく設定している。この結
果、ディスク部は厚肉構造となり、基本直径が短くなっ
た分遠心力の影響も小さくなり、振動特性が向上するも
のである。In the invention (2) of the present invention, the inclination angle of the disk is set to be larger than the conventional 6 to 10 degrees, and the basic diameter is set to 400 mm, which is smaller than the conventional one. As a result, the disk portion has a thick structure, and the influence of the centrifugal force is reduced by the reduced basic diameter, thereby improving the vibration characteristics.
【００２５】本発明の（３）では、軸受スパンを従来よ
りも短くして８００mm以下とし、Ｌ／Ｄも従来の６．６
〜７．５の範囲から６．０未満として小さくしたので回
転軸の振動特性がより確実に向上し、高速回転が可能と
なるものである。In (3) of the present invention, the bearing span is made shorter than the conventional one to 800 mm or less, and the L / D is 6.6 of the conventional type.
The vibration characteristic of the rotating shaft is more reliably improved, and high-speed rotation is possible, since the range is reduced from the range of 7.5 to less than 6.0.
【００２６】本発明の（４）では、上記（１）〜（３）
の発明のすべての要件を備えたものであり、ディスク部
の強度向上と回転軸の強度及び振動特性が総合的に向上
し、１５０００〜１８０００回転／分の高速回転を可能
とするバレル型圧縮機駆動用背圧タービンが確実に実現
できるものである。In (4) of the present invention, the above (1) to (3)
A barrel-type compressor which has all the requirements of the invention of the present invention, improves the strength of the disk portion, improves the strength and vibration characteristics of the rotating shaft comprehensively, and enables high-speed rotation of 15,000 to 18000 rpm. A driving back-pressure turbine can be reliably realized.
【図１】本発明の実施の一形態に係るバレル型圧縮機駆
動用背圧タービンの断面図である。FIG. 1 is a cross-sectional view of a back-pressure turbine for driving a barrel-type compressor according to an embodiment of the present invention.
【図２】図１に示す動翼のディスク部の形状を示す図で
ある。FIG. 2 is a view showing a shape of a disk portion of the rotor blade shown in FIG. 1;
【図３】本発明の実施の一形態に係る背圧タービンの翼
の配置を示す図で、（ａ）は静翼、（ｂ）は動翼を示
す。FIGS. 3A and 3B are diagrams showing an arrangement of blades of a back pressure turbine according to one embodiment of the present invention, wherein FIG. 3A shows stationary blades and FIG.
１０ ケーシング １１ 回転軸 １２，１３ ジャーナル軸受 １４ スラスト軸受 １５ １段静翼 １６ １段動翼 １７ ２段静翼 １８ ２段動翼 ２０，２１ ディスク部 ２２，２３ シール部 ２４ 蒸気入口 ２５ ノズル部 ２６ 蒸気通路 ２７ 蒸気出口 DESCRIPTION OF SYMBOLS 10 Casing 11 Rotating shaft 12, 13 Journal bearing 14 Thrust bearing 15 1st stage stationary blade 16 1st stage rotating blade 17 2nd stage stationary blade 18 2nd stage rotating blade 20, 21 Disk part 22, 23 Seal part 24 Steam inlet 25 Nozzle part 26 Steam passage 27 Steam exit
Claims (4)
されるタービン部に流し回転軸を回転させて圧縮機を駆
動するバレル型圧縮機駆動用背圧タービンにおいて、前
記静翼及び動翼は２段で構成されると共に、回転数は１
５０００〜１８０００回転／分であることを特徴とする
バレル型圧縮機駆動用背圧タービン。A back pressure turbine for driving a barrel-type compressor, wherein steam is guided into a barrel and is caused to flow through a turbine section comprising a stationary blade and a moving blade, and a rotating shaft is rotated to drive a compressor. The rotor blade is composed of two stages, and the rotation speed is 1
A back-pressure turbine for driving a barrel-type compressor, wherein the speed is 5,000 to 18,000 rpm.
心線と直交する線分に対する傾斜角度は２０〜２２度と
し、前記ディスクの基本直径は４００mm以下としたこと
を特徴とする請求項１記載のバレル型圧縮機駆動用背圧
タービン。2. The disk according to claim 1, wherein a tilt angle of the disk to which the rotor blade is attached is 20 to 22 degrees with respect to a line perpendicular to an axis of the disk, and a basic diameter of the disk is 400 mm or less. Back pressure turbine for barrel type compressor drive.
以下で、軸受スパンをＬとし回転軸の径をＤとしてＬ／
Ｄを６．０未満とすることを特徴とする請求項１記載の
バレル型圧縮機駆動用背圧タービン。3. A span between bearings of the rotating shaft is 800 mm.
In the following, L / L is the bearing span and D is the diameter of the rotating shaft.
The back pressure turbine for driving a barrel type compressor according to claim 1, wherein D is less than 6.0.
されるタービン部に流し回転軸を回転させて圧縮機を駆
動するバレル型圧縮機駆動用背圧タービンにおいて、前
記静翼及び動翼は２段で構成されると共に、前記回転軸
の回転数は１５０００〜１８０００回転／分であり、軸
受間のスパンは８００mm以下で、軸受スパンをＬとし回
転軸の径をＤとしてＬ／Ｄを６．０未満に設定し、更に
前記動翼が取付けられるディスクの軸中心線と直交する
線分に対する傾斜角度は２０〜２２度とし、前記動翼の
基本直径は４００mm以下としたことを特徴とするバレル
型圧縮機駆動用背圧タービン。4. A barrel type compressor back pressure turbine for driving steam by introducing steam into a barrel, and flowing the steam into a turbine section comprising a stationary blade and a moving blade to rotate a rotating shaft to drive the compressor. The rotor blade is composed of two stages, the number of revolutions of the rotating shaft is 15,000 to 18,000 rpm, the span between bearings is 800 mm or less, the bearing span is L, and the diameter of the rotating shaft is D. D is set to less than 6.0, the inclination angle with respect to a line perpendicular to the axis of the disk to which the moving blade is attached is set to 20 to 22 degrees, and the basic diameter of the moving blade is set to 400 mm or less. Back pressure turbine for barrel type compressor drive.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2000278223A JP2002089202A (en) | 2000-09-13 | 2000-09-13 | Back pressure turbine for driving barrel-type compressor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2000278223A JP2002089202A (en) | 2000-09-13 | 2000-09-13 | Back pressure turbine for driving barrel-type compressor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JP2002089202A true JP2002089202A (en) | 2002-03-27 |
Family
ID=18763419
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP2000278223A Withdrawn JP2002089202A (en) | 2000-09-13 | 2000-09-13 | Back pressure turbine for driving barrel-type compressor |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP2002089202A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2017053356A (en) * | 2010-09-21 | 2017-03-16 | パルマー ラボ，エルエルシー | High efficiency power production method, assembly and system |
-
2000
- 2000-09-13 JP JP2000278223A patent/JP2002089202A/en not_active Withdrawn
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2017053356A (en) * | 2010-09-21 | 2017-03-16 | パルマー ラボ，エルエルシー | High efficiency power production method, assembly and system |
| JP2018159381A (en) * | 2010-09-21 | 2018-10-11 | パルマー ラボ，エルエルシー | High efficiency power production method, assembly and system |
| US10927679B2 (en) | 2010-09-21 | 2021-02-23 | 8 Rivers Capital, Llc | High efficiency power production methods, assemblies, and systems |
| JP2021050741A (en) * | 2010-09-21 | 2021-04-01 | パルマー ラボ，エルエルシー | High efficiency power production method, assembly and system |
| US11459896B2 (en) | 2010-09-21 | 2022-10-04 | 8 Rivers Capital, Llc | High efficiency power production methods, assemblies, and systems |
| US11859496B2 (en) | 2010-09-21 | 2024-01-02 | 8 Rivers Capital, Llc | High efficiency power production methods, assemblies, and systems |
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| A300 | Withdrawal of application because of no request for examination |
Free format text: JAPANESE INTERMEDIATE CODE: A300 Effective date: 20071204 |