Cooling structure for a gas turbine

Abstract: In a cooling structure for a gas turbine, cooling air diffusion holes are formed from inner surface to outer surface of a platform so as to open from high pressure side blade surface of a moving blade offset in a direction toward low pressure side blade surface of adjacent moving blade confronting the high pressure side blade surface, in a direction of primary flow.

Description: FIELD OF THE INVENTION The present invention relates to a cooling structure for a gas turbine according to the preamble portion of claim 1. More particularly, this invention relates to a cooling structure for a gas turbine improved in the film cooling structure for high temperature members. BACKGROUND OF THE INVENTION To enhance the heat efficiency of gas turbine used in generator or the like, it is effective to raise the temperature of the operating high temperature gas at the turbine inlet, but the turbine inlet temperature cannot be merely raised because the heat resisting performance of turbine materials exposed to high temperature gas (hereinafter called high temperature members), including the turbine moving blades and turbine stationary blades, is specified by the physical properties of the materials. Accordingly, it has been attempted to enhance the heat efficiency within the range of heat resisting performance of high temperature members by raising the turbine inlet temperature while cooling the turbine high temperature members by cooling medium such as cooling air. Cooling methods of high temperature members include the convection heat transfer type of passing cooling air into the high temperature members, and keeping the surface temperature of high temperature members lower than the temperature of high temperature gas by heat transfer from high temperature members to cooling air, the protective film type of forming a compressed air film of low temperature on the surface of high temperature members, and suppressing heat transfer from the high temperature gas to the high temperature member surface, and the cooling type combining these two types. The convection heat transfer type includes convection cooling and blow (collision jet) cooling, and the protective film type includes film cooling and exudation cooling, and among them, in particular, the exudation cooling is most effective for cooling the high temperature members. However, it is difficult to process the porous material used in exudation cooling, and uniform exudation is not expected when pressure distribution is not uniform, and therefore among the practical methods, the cooling structure by film cooling is most effective for cooling high temperature members, and in the gas turbine of high heat efficiency, the cooling structure combining the convection cooling and film cooling is widely employed. In the cooling structure by film cooling, meanwhile, it is required to form diffusion holes for blowing out cooling air, by discharge processing or the like, from the inner side of the high temperature members or the back side of the surface exposed to high temperature gas, to the surface exposed to the high temperature gas. Hitherto, the diffusion holes were formed so as to open toward the direction of the primary flow of high temperature gas flowing along the high temperature members. However, the flow of high temperature gas is disturbed to form complicated secondary flow advancing in a direction different from the primary flow due to various factors, such as sealing air leaking between the platform of turbine moving blade and inner shroud of the turbine stationary blade, air leaking between the split ring which is the peripheral wall disposed opposite to the tip side (the leading end in the radial direction) of the turbine moving blade and the outer shroud of the turbine stationary blade, and pressure difference after collision against the passage wall such as blade, split ring, platform, and shroud. Accordingly, the cooling air blown out along the primary flow direction is scattered by the secondary flow, and the cooling effect on the high temperature members cannot be exhibited sufficiently. US-A-5 533 864 discloses a conventional gas turbine stationary cooling blade which is provided with a plurality of diffusion holes formed in the blade and in sections of the outer and inner shroud for achieving film cooling. US-A-5 382 135 discloses a rotor blade with a cooled integral platform in which the diffusion holes for cooling the platform are arranged in a similar manner as in example 1 described further below. US-A-5 503 529 discloses a gas turbine engine turbine airfoil with a plurality of ejection slots which are arranged in a column through the first side wall. At least some of the ejection slots are inclined at an acute ejection angle which varies in magnitude for preferably matching the respective inclination of combustion gas streamlines flowable over the airfoil surface. SUMMARY OF THE INVENTION It is an object of the present invention to provide a cooling structure for a gas turbine enhanced in the cooling effect of film cooling of the shroud of the turbine stationary blade as compared to the conventional art. According to the present invention there is provided a cooling structure for a gas turbine as defined in claim 1. As the cooling medium, cooling air may be used, and the cooling air may be obtained, for example, by extracting part of the air supplied in the compressor of the gas turbine, and cooling the extracted compressed air by a cooler. The secondary flow is caused by leak of sealing air, or due to pressure difference in the passage after high temperature gas collides against the blade, and the flow direction may be determined by flow analysis or experiment using actual equipment. The direction nearly coinciding with the secondary flow direction is in a range of about ±20 degrees of the secondary flow direction, preferably in a range of ±10 degrees, and most preferably in a range of ±5 degrees. Other objects and features of this invention will become apparent from the following description with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS Fig. 1 is a semi-sectional view showing an entire gas turbine according to cooling structure in a first embodiment of the invention. Fig. 2A and Fig. 2B are diagrams showing flow of high temperature gas in platform in a first example to explain certain aspects of the invention. Fig. 3A to Fig. 3C explain secondary flow at the blade surface of the moving blade. Fig. 4 is a diagram showing platform forming diffusion holes of cooling air in the first example. Fig. 5A and Fig. 5B are diagrams showing the detail of the air diffusion holes. Fig. 6A and Fig. 6B are explanatory diagrams of horseshoe vortex flow in platform in a second example to explain certain aspects of the invention. Fig. 7 is a diagram showing platform forming diffusion holes of cooling air in the second example. Fig. 8 is a perspective view showing flow of high temperature gas in shroud of stationary blade in the first embodiment of the invention. Fig. 9A and Fig. 9B are diagrams showing shroud forming diffusion holes of cooling air in the first embodiment. Fig. 10A and Fig. 10B are diagrams showing moving blade forming diffusion holes of cooling air in a third example. Fig. 11A and Fig. 11B are diagrams showing stationary blade forming diffusion holes of cooling air in a second embodiment. DETAILED DESCRIPTION Examples and embodiments of cooling structure for a gas turbine according to the invention are specifically described while referring to the accompanying drawings. It must be noted, however, that the invention is not limited to the illustrated embodiments alone. Fig. 1 is a partial longitudinal sectional view of a gas turbine 10 for explaining the cooling structure for a gas turbine in a first embodiment of the invention. The gas turbine 10 comprises a compressor 20 for compressing supplied air, a combustor 30 for injecting fuel to the compressed air from the compressor 20 and generating high temperature combustion gas (high temperature gas), and a turbine 40 for generating a rotary driving force by the high temperature gas generated in the combustor 30. The turbine 10 includes a cooler, not shown, for extracting part of compressed air from the compressor 20, and sending out the extracted compressed air to a moving blade 42, a stationary blade 45, and a platform 43 of the turbine 40, and also to an inner shroud 46 and an outer shroud 47 of the stationary blade 45. A moving blade body 41 of the turbine 40, as shown in Fig. 2A, is composed of the moving blade 42 and the platform 43 which is coupled to a rotor not shown, and the direction of primary flow V1 of high temperature gas in the moving blade body 41 is the direction of blank arrow shown in Fig. 2A. Fig. 2B is a sectional view along the surface including the outer surface of the platform 43 in Fig. 2A, and the direction of primary flow V1 of high temperature gas shown in Fig. 2A is more specifically a direction nearly parallel to the camber line C of the moving blade 42. In the platform 43, in order to protect from high temperature gas, diffusion holes for film cooling are formed, and the diffusion holes for film cooling were, hitherto, formed along the direction of primary flow V1, that is, in a direction parallel to the camber line C, so as to incline and penetrate at the outer surface 43a side of flow of high temperature gas from the back side (inner side) 43b of the platform 43. Thus, by opening the diffusion holes in the direction of primary flow V1 of high temperature gas, the cooling air blown out from the diffusion holes to the outer surface 43a of the platform 43 runs along the flow direction (primary flow direction V1) of high temperature gas, and hence the cooling air is not disturbed in its flow direction by the flow of high temperature gas, and therefore it has been considered that the outer surface 43a of the platform 43 is protected from burning by high temperature gas. In the gas turbine 10, the diffusion holes are formed along the direction of secondary flow V2 of high temperature gas, from the inner surface 43b to outer surface 43a of the platform 43. More specifically, in the direction of primary flow V1, that is, in a direction parallel to the camber line C, they are formed from the inner surface 43b to outer surface 43a of the platform 43 so as to open offset in a direction toward the low pressure side blade surface 42b of the adjacent moving blade 42 confronting the high pressure side blade surface 42a from the high pressure side blade surface 42a of the moving blade 42. Mechanism of formation of secondary flow of high temperature gas is explained on the basis of the results of studies by the present inventors. First, on the platform 43, sealing air (purge air) V3 escapes from a gap to the inner shroud 44 of the stationary blade at the upstream side of high temperature gas, and the relative flow direction of the sealing air V3 to the moving blade body 41 rotating in the direction of arrow R, as shown in Fig. 2B, is a direction offset from the camber line C toward the lowpressure side blade surface 42b of the adj acent moving blade 42 confronting the high pressure side blade surface 42a from the high pressure side blade surface 42a of the moving blade 42. By the flow of sealing air V3, the flow direction of primary flow V1 of high temperature gas is changed, and the changed flow is the secondary flow V2. The secondary flow V2 is not produced by the sealing air V3 only. That is, in Fig. 3A which is a sectional view along line A-A in Fig. 2B, the high temperature gas flowing into the moving blade body 41 collides against the high pressure side blade surface 42a of the moving blade 42, and the colliding high temperature gas produces a flow along a split ring 48 disposed at the tip side (outside) of the moving blade 42 along the high pressure side blade surface 42a, and a flow toward the platform 43. The flow toward the split ring 48 flows into the low pressure side blade surface 42b of the moving blade 42 from a gap between the outer end of the moving blade 42 to the split ring 48. On the other hand, the flow toward the platform 43 side flows on the platform 43 from the high pressure side blade surface 42a of the moving blade 42 toward the lowpressure side blade surface 42b of the adj acent moving blade 42 confronting the high pressure side blade surface 42a, and climbs up in the outside direction along the low pressure side blade surface 42b of the adjacent moving blade 42. That is, the flow of high temperature gas in the high pressure side blade surface 42a of each moving blade 42 is as indicated by arrow in Fig. 3B, and the flow of high temperature gas in the low pressure side blade surface 42b is as indicated by arrow in Fig. 3C. The flow of high temperature gas on the platform 43 is the secondary flow V2 in Fig. 2B. Thus, along the direction of secondary flow V2 on the platform 43, a mode of forming diffusion holes 43c is shown in Fig. 4, Fig. 5A, and Fig. 5B. As shown in Fig. 4, Fig. 5A, and Fig. 5B, in order to open the diffusion holes 43c offset in a direction from the high pressure side blade surface 42a of the moving blade 42 toward the low pressure side blade surface 42b of the adjacent moving blade 42 confronting the high pressure side blade surface 42a, in a direction parallel to the camber line C, they are disposed from the inner surface 43b (see Fig. 5B) to the outer surface 43a (see Fig. 5B) of the platform 43, and therefore the cooling air blow out from the outer surface 43a of the platform 43 runs along the secondary flow V2 of high temperature gas on the platform 43, and the cooling air is not disturbed by the secondary flow V2 of high temperature gas, forming a cooling air film on the outer surface 43a, so that a desired cooling effect on the platform 43 is obtained. Diffusion holes 43c shown in Fig. 4 correspond to the secondary flow V2 shown in Fig. 2B, and the direction of the diffusion holes in the cooling structure for a gas turbine of the invention is not always limited to the configuration shown in Fig. 4, but may be free as far as corresponding to the direction of secondary flow V2 determined by flow analysis or experiment. Fig. 5A shows diffusion holes 43c formed on the outer surface 43a of the platform 43, and Fig. 5B is a sectional view along line D-D in Fig. 5A. As shown in Fig. 5A, the opening end on the outer surface 43a of the platform 43 of the diffusion holes 43c is shaped like a funnel with the downstream side slope 43d of the secondary flow V2 le ss steep than the upstream side slope 43e, and according to this structure, since the cooling air (50 in Fig. 5B) blown out from the diffusion holes 43c flows along the downstream side slope 43d less steep than the upstream side of the secondary flow V2, at this opening end, it flows more smoothly along the secondary flow V2 of high temperature gas, and the reliability of formation of cooling air film on the outer surface 43a of the platform 43 is enhanced, and the cooling effect on the platform 43 is further improved, but the cooling structure for the gas turbine of the invention is not always limited to formation of such opening end. Fig. 6A and Fig. 6B are diagrams showing flow of high temperature gas near the front end (high pressure gas upstream side end of moving blade 42) 42c of the moving blade 42 for explaining the cooling structure for a gas turbine of the invention in a second example, and Fig. 7 is a diagram showing the cooling structure of platform 43 of gas turbine in the second example. According to the first example, on the platform 43, the primary flow V1 of high temperature gas runs nearly parallel to the camber line C of the moving blade 42. At the front end 42c of the moving blade 42, as shown in a sectional view in Fig. 6B, horseshoe vortex V4 is formed as secondary flow V2 of high temperature gas. This horseshoe vortex V4 is formed when part of the primary flow V1 of high temperature gas flowing into the moving blade 42 collides against the front end 42c of the moving blade 42, moves into the root portion direction (direction of platform 43) of the moving blade 42 along the moving blade 42c, runs on the platform 43 in a direction departing from the moving blade 42, and gets into the direction of the low pressure moving blade surface 42b of the moving blade 42. According to the cooling structure of the gas turbine in the second example, diffusion holes 43f of cooling air of the platform 43 near the front end 42c of the turbine moving blade are formed from the inner surface 43b (see Fig. 5B) to the outer surface 43a (see Fig. 5B) of the platform 43 so as to open along the flow direction of the horseshoe vortex V4 flowing in the direction departing from the front end 42c of the moving blade 42 at the platform 43. Since the cooling air diffusion holes 43f are thus formed, the cooling air blown out from the outer surface 43a of the platform 43 runs along the horseshoe vortex V4 of high temperature gas on the platform 43, and the cooling air is not disturbed by the horseshoe vortex V4 of high temperature gas, thereby forming a cooling air film on the outer surface 43a, so that a desired cooling effect on the platform 43 near the front end 42c of the moving blade 42 may be obtained. At the opening end of the diffusion holes 43f in the second example, same as in the case of the diffusion holes 43c in the first example, the downstream side slope of the horseshoe vortex V4 is preferred to be formed like a funnel of a less steep slope than the upstream side slope. It may be also combined with the first example. Fig. 8, Fig. 9A, and Fig. 9B are diagrams showing flow of high temperature gas in a stationary blade body 44 for explaining the cooling structure for a gas turbine in a first embodiment of the invention, and Fig. 9A specifically shows cooling air diffusion holes 46c in an inner shroud 46 of the stationary blade body 44, and Fig. 9B specifically shows cooling air diffusion holes 47c in an outer shroud 47 of the stationary blade body 44. The stationary blade body 44 of the turbine 40, as shown in Fig. 8, is composed of stationary blade 45, and outer shroud 47 and inner shroud 46 fixed in a casing not shown, and the direction of primary flow V1 of high temperature gas in this stationary blade body 44 is the direction of blank arrow. Fig. 9A is a sectional view along the side including the surface of the inner shroud 46 in Fig. 8, and Fig. 9B is a sectional view along the side including the surface of the outer shroud 47 in Fig. 8. In these inner and outer shrouds 46, 47, the direction of primary flow V1 of high temperature gas is a direction nearly parallel to the camber line C of the stationary blade 45 on the surface of the shrouds 46, 47. On the other hand, same as the secondary flow V2 caused by the moving blade 42 explained in the first example, on the stationary blade body 44, too, a secondary flow V2 is formed by the stationary blade 45, and the direction of the second flow V2 is, same as in the first example, in the direction of primary flow V1, that is, in a direction parallel to the camber line C, offset in a direction from the high pressure side blade surface 45a of the stationary blade 45 toward the low pressure side blade surface 45b of the adjacent stationary blade 45 confronting the high pressure side blade surface 45a. In the first embodiment, diffusion holes 46c of cooling air of the inner shroud 46 and diffusion holes 47c of cooling air of the outer shroud 47 are formed, as shown in Fig. 9A and Fig. 9B respectively, so as to open in a direction offset from the high pressure side blade surface 45a of the stationary blade 45 toward the low pressure side blade surface 45b of the adjacent stationary blade 45, along the direction of secondary flow V2 of high pressure gas, that is, in the direction of primary flow V1 or direction parallel to the camber line C. The cooling air blown out from thus formed diffusion holes 46c, 47c runs along the secondary flow V2 of high temperature gas on the inner shroud 46 and outer shroud 47, and the cooling air is not disturbed by the secondary flow V2 of high temperature gas, thereby forming a cooling air film, so that a desired cooling effect is obtained on the inner shroud 46 and outer shroud 47. In Fig. 9A and Fig. 9B, only one diffusion hole, 46c, 47c is shown in each shroud 46, 47, but this is only for simplifying the drawing, and actually plural diffusion holes 46c, 47c are formed along the secondary flow V2 in the entire structure of the shrouds 46, 47. At the opening ends of the diffusion holes 46c, 47c, same as in the case of the diffusion holes 43c in the first example, the downstream side slope of the secondary flow V2 is preferred to be formed like a funnel of a less steep slope than the upstream side slope. It may be also combined with the first example or the second example. Fig. 10A and Fig. 10B show a third example to explain aspects of the invention, relating to cooling air diffusion holes 42d in high pressure side blade surface 42a and low pressure side blade surface 42b of moving blade 42. The diffusion holes 42d are formed so as to open along the secondary flow V2 of high temperature gas at the blade surfaces 42a, 42b of the moving blade 42 shown in Fig. 3B and Fig. 3C. The cooling air blown out from thus formed diffusion holes 42d runs along the secondary flow V2 of high temperature gas on the high pressure side blade surface 42a and low pressure side blade surface 42b, and the cooling air is not disturbed by the secondary flow V2 of high temperature gas, thereby forming a cooling air film, so that a desired cooling effect is obtained on the high pressure side blade surface 42a and low pressure side blade surface 42b of the moving blade 42. At the opening ends of the diffusion holes 42d of the fourth embodiment, same as in the case of the diffusion holes 43c in the first example, the downstream side slope of the secondary flow V2 is preferred to be formed like a funnel of a less steep slope than the upstream side slope. It may be also combined with at least one of the first example, the second example and the first embodiment. Fig. 11A and Fig. 11B show a second embodiment of the invention, relating to cooling air diffusion holes 45c in high pressure side blade surface 45a and low pressure side blade surface 45b of stationary blade 45. The diffusion holes 45c are formed so as to open along the secondary flow V2 of high temperature gas at the high pressure side blade surface 45a and low pressure side blade surface 45b of the stationary blade 45 as well as the secondary flow V2 of high temperature gas at each blade surface 42a, 42b of the moving blade 42. The cooling air blown out from thus formed diffusion holes 45c runs along the secondary flow V2 of high temperature gas on the high pressure side blade surface 45a and low pressure side blade surface 45b, and the cooling air is not disturbed by the secondary flow V2 of high temperature gas, thereby forming a cooling air film, so that a desired cooling effect is obtained on the high pressure side blade surface 45a and lowpressure side blade surface 45b of the stationary blade 45. At the opening ends of the diffusion holes 45c of the second embodiment, same as in the case of the diffusion holes 43c in the first example, the downstream side slope of the secondary flow V2 is preferred to be formed like a funnel of a less steep slope than the upstream side slope. It may be also combined with the first embodiment. According to the cooling structure for a gas turbine of the invention, the cooling medium blown out from the diffusion holes of the shroud of the turbine stationary blade as high temperature member runs along the secondary flow of high temperature gas flowing on the outer surface of the shroud, and the cooling medium is not disturbed by the secondary flow of high temperature gas, and an air film is formed on the outer surface, so that a desired cooling effect on the shroud of the turbine stationary blade is obtained. The shroud of the turbine stationary blade includes both outside shroud on the outer periphery and inner shroud on the inner periphery. According to the cooling structure for a gas turbine of the invention, the cooling medium blown out from the diffusion holes of the shroud runs along the secondary flow toward the low pressure side blade surface of the turbine stationary blade rather than the primary flow direction of high temperature gas along the camber line of the turbine stationary blade, and therefore the cooling medium is not disturbed by the secondary flow of high temperature gas, and an air film is formed on the outer surface, so that a desired cooling effect on the shroud of the turbine stationary blade is obtained. According to the cooling structure for a gas turbine of the invention, the cooling medium blown out from the diffusion holes near the front end of the turbine stationary blade of the shroud runs along the direction of the secondary flow of horseshoe vortex formed in the vicinity of the front end, and therefore the cooling medium is not disturbed by the secondary flow of high temperature gas, and an air film is formed on the outer surface, so that a desired cooling effect on the shroud of the turbine stationary blade is obtained. According to the cooling structure for a gas turbine of the invention, the cooling medium blown out from the diffusion holes of the turbine stationary blade as one of high temperature members runs along the secondary flow of high temperature gas flowing on the outer surface of the turbine blade, and the cooling medium is not disturbed by the secondary flow of high temperature gas, and an air film is formed on the outer surface, so that a desired cooling effect on the turbine blade is obtained. According to the cooling structure for a gas turbine of the invention, the cooling medium blown out from the diffusion holes in the upper part of the high pressure side blade surface and in the lower part of the low pressure side blade surface of the turbine stationary blades runs along the direction of the secondary flow formed from the primary flow direction of high temperature gas along the direction parallel to the axis of the turbine toward a direction offset above the blades, and therefore the cooling medium running in this area is not disturbed by the secondary flow of high temperature gas, and an air film is formed on the outer surface, so that a desired cooling effect on this area of the turbine blades is obtained, and moreover the cooling medium blown out from the diffusion holes in the lower part of the high pressure side blade surface and in the upper part of the low pressure side blade surface of the turbine blades runs along the direction of the secondary flow formed from the primary flow direction of high temperature gas along the direction parallel to the axis of the turbine toward a direction offset beneath the blades, and therefore the cooling medium running in this area is not disturbed by the secondary flow of high temperature gas, and an air film is formed on the outer surface, so that a desired cooling effect on this area of the turbine blades is obtained. According to the cooling structure for a gas turbine of the invention, the cooling medium blown out from the diffusion holes flows along the downstream side slope which is less steep than the upstream side slope of the secondary flow at the opening end, and hence it runs more smoothly along the secondary flow direction of high temperature gas, and the reliability of formation of film on the surface of high temperature members is enhanced, and the cooling effect on the high temperature members may be further enhanced.

Claims: A cooling structure for a gas turbine including multiple diffusion holes (45c,46c,47c) formed in high temperature members (45,47,46) of the gas turbine (10) for blowing a cooling medium to outer surfaces of the high temperature members for film cooling thereof, wherein said diffusion holes are formed so as to open in a direction nearly coinciding with a secondary flow direction (V2) of high temperature gas flowing on the outer surfaces of the high temperature members, and wherein the high temperature members include a shroud (46,47) of a turbine stationary blade (45); characterized in that said diffusion holes (46c,47c) in said shroud (46,47) are formed so as to open in a direction running from a high pressure side blade surface (45a) of the turbine stationary blade (45) to the low pressure side blade surface (45b) of an adjacent turbine stationary blade (45) confronting the high pressure side blade surface (45a), and so as to be offset from the primary flow direction (V1) of high temperature gas along the camber line (C) of the turbine stationary blade (45). The cooling structure for a gas turbine according to claim 1, wherein the secondary flow (V2) includes a horseshoe vortex (V4) of high temperature gas formed near the front end of the turbine stationary blade (45), and the diffusion holes near the front end of the turbine stationary blade (45) are formed so as to open along the flow direction of the horse shoe vortex (V4). The cooling structure for a gas turbine according to claim 1 or 2, wherein the high temperature members include the stationary turbine blades (45). The cooling structure for a gas turbine according to claim 3, wherein the diffusion holes (45c) in the upper part of the high pressure side blade surface (45a) and in the lower part of the low pressure side blade surface (45b) of the stationary turbine blades (45) are formed so as to open offset above the stationary turbine blades (45) from the primary flow direction (V1) of high temperature gas along the axial direction of the turbine (10), and the diffusion holes (45c) in the lower part of the high pressure side blade surface (45a) and in the upper part of the low pressure side blade surface (45b) are formed so as to open offset beneath the stationary turbine blades (45) from the primary flow direction (V1) of high temperature gas along the axial direction of the turbine (10). The cooling structure for a gas turbine according to any one of claims 1 to 4, wherein the opening end of the diffusion holes is formed like a funnel with the downstream side slope of the secondary flow less steep than the upstream side slope. The cooling structure for a gas turbine according to any one of claims 1 to 5, wherein the direction nearly coinciding with the secondary flow direction (V2) is in a range of about ±20 degrees of the secondary flow direction, preferably in the range of ±10 degrees, and most preferably in the range of ±5 degrees.

Inventors: AOKI HIROYUKI, KUBOTA JUN, KUWABARA MASAMITSU, TOMITA YASUOKI, TORII SHUNSUKE, AOKI, HIROYUKI, KUBOTA, JUN, KUWABARA, MASAMITSU, TOMITA, YASUOKI, TORII, SHUNSUKE, Aoki, Hiroyuki, Mitsubishi Heavy Industries, Kubota, Jun, Mitsubishi Heavy Industries, Kuwabara, Masamitsu, Mitsubishi Heavy Industries, Tomita, Yasuoki, Mitsubishi Heavy Industries, Torii, Shunsuke, Mitsubishi Heavy Industries
Applicants: MITSUBISHI HEAVY IND LTD, MITSUBISHI HEAVY INDUSTRIES, LTD.
Application year: 2001
Main classification: F01D5
IPC codes: F01D5, F01D25, F01D9