Gas turbine combustor

Abstract: In gas turbine combustor in which combustion air flows on outer periphery of cylinder body and turns to enter the cylinder body while being mixed with fuel in main burner to form pre-mixture, there is provided upstream of the main burner 101 in the combustor 103 a rectifier 106 or 108 for rectifying the combustion air so as to make flow velocity of the combustion air uniform, thereby shortcomings in the prior art of concentration non-uniformity of the pre-mixture of main fuel and combustion air, high concentration of NO x generated from the main burner 101 in combustion, etc. are eliminated and larger combustion range to maintain stable combustion is attained.

Description: Field of the Invention: The present invention relates to a combustor of gas turbine for a thermal power plant and the like. Description of the Prior Art: Fig. 2 is an explanatory view of a prior art premixed flame low NO x type combustor of gas turbine for a thermal power plant and the like. In this figure, the gas turbine combustor has therein a combustor 203 of cylinder body and eight pieces of main burners 201 are disposed in the combustor 203 around central axis thereof. Main fuel supplied from main fuel nozzles and combustion air are mixed to form a pre-mixture, which is burned in the combustor 203 with a pilot of a pilot fuel supplied from a pilot fuel nozzle 202. The combustion air flows on an outer periphery of the combustor 203 and turns 180° at an air inflow portion 205 to enter the combustor 203. In Fig. 2, numeral 204 designates a pilot air swirler, which is disposed for supplying combustion air for burning the pilot fuel. In the prior art gas turbine combustor as mentioned above, the combustion air flows on the outer periphery of the combustor 203 of cylinder body and then turns 180° at the air inflow portion 205 to enter the combustor 203, hence the combustion air, so turned, is biased to the central portion, so that velocity distribution of the combustion air in the combustor 203 in the cross section A-A of Fig. 2(a) tends to become faster at the central portion of the combustor 203 and slower at the peripheral portion of same. If such biasing occurs in the velocity distribution of the combustion air in the combustor 203, concentration of the premixed fuel of the main fuel and the combustion air becomes non-uniform and there arise shortcomings such that NO x generated at the main burners 201 in the combustion becomes high in concentration, combustion range for effecting a stable combustion in the combustor 203 becomes narrow, etc. US-A-4 704 869 describes a prior art gas turbine combustor with a plurality of burner units each having an inner tube defining a combustion chamber therein and an outer tube coaxially surrounding the inner tube. Fuel is injected into the head portion of the inner tube and is burned in the combustion chamber to produce hot combustion gases. Combustion air is supplied through an annular-cylindrical passage between the inner and outer tubes from the area around the tail tube to the head portion of the inner tube. A flow-uniformalizing tube is coaxially disposed between the inner and outer tubes to cooperate with the inner tube to define therebetween an air passage. The flow-uniformalizing tube imparts a greater flow resistance to air flow from the backside of the tail tube than to the air flow from the side thereof diametrically remote from the backside so that the flow velocity of the air flowing through the air passage is substantially uniformalized in the circumferential direction of the inner tube. SUMMARY OF THE INVENTION. It is the object of the present invention to provide a gas turbine combustor of the basic type shown in figure 2 which is improved so that the velocity distribution in the portion downstream of the burners is more uniform. According to the present invention there is provided a gas turbine combustor with the features of claim 1. Preferred embodiments of the gas turbine combustor are defined in the dependent claims. In the gas turbine combustor according to the present invention as mentioned above, there is provided upstream of the main burner the rectifier for rectifying the combustion air flowing on the outer periphery of the cylinder body of the combustor and turning to enter the cylinder body so as to make the flow velocity distribution of the combustion air uniform, thereby the flow rate of the combustion air upstream of the main burner in the cylinder body of the combustor becomes uniform. Also, in the gas turbine combustor according to a preferred embodiment of the present invention there are provided a plurality of said main burners around a central axis of said cylinder body and said rectifier is such one as having an opening formed in a ring shape (annular) so as to close a central portion of said cylinder body. According to the present gas turbine combustor, by use of a simple structure of the rectifier, the combustion air is rectified so that biasing of the combustion air toward the central portion of the cylinder body of the combustor is corrected and a rectifying effect for making the flow velocity in the cylinder body uniform is obtained. Also, the gas turbine combustor according to another preferred embodiment of the present invention there are provided a plurality of said main burners around a central axis of said cylinder body and said rectifier is such one as shaving a plurality of openings, each formed in a round hole shape corresponding to said plurality of main burners, positioned upstream of said plurality of main burners. According to the present gas turbine combustor, the rectifier for rectifying the combustion air to be led into the main burner has a higher rectifying function so that biasing of the combustion air toward the central portion of the cylinder body of the combustor is corrected and a higher rectifying effect for making the flow velocity in the cylinder body uniform is obtained. BRIEF DESCRIPTION OF THE DRAWINGS: Fig. 1 is an explanatory view of a gas turbine combustor of one embodiment according to the present invention, wherein Fig. 1(a) is a longitudinal cross sectional view thereof, Fig. 1 (b) is a cross sectional view showing one example of rectifier taken on line B-B of Fig. 1(a), Fig. 1(c) is an explanatory view showing an effect of the rectifier and Fig. 1(d) is a cross sectional view showing another example of rectifier taken on line B-B of Fig. 1(a). Fig. 2 is an explanatory view of a prior art gas turbine combustor, wherein Fig. 2(a) is a longitudinal cross sectional view thereof, Fig. 2(b) is a cross sectional view taken on line A-A of Fig. 2(a) and Fig. 2(c) is an explanatory view showing an effect thereof. DESCRIPTION OF THE PREFERRED EMBODIMENTS: Fig. 1 is an explanatory view of a premixed flame low NO x type combustor of gas turbine of one embodiment according to the present invention. In this figure, the gas turbine combustor of the embodiment is a combustor of a gas turbine used for a thermal power plant and the like, and numeral 101 designates a main burner of the gas turbine combustor, numeral 102 designates a pilot fuel nozzle of the gas turbine combustor, numeral 103 designates a combustor cylinder body, numeral 104 designates a pilot air swirler, which is disposed for supplying a combustion air for burning a pilot fuel, numeral 105 designates an air inflow portion, at which the combustion air, flowing on an outer periphery of the combustor cylinder body 103, turns 180° to enter the combustor cylinder body 103 and numeral 106 designates a rectifier, which is disposed at an inlet of the combustor cylinder body 103 for rectifying the combustion air flowing through the air inflow portion 105 to enter the combustor cylinder body 103 so that flow velocity of the combustion air in the combustor cylinder body 103 is made uniform substantially. In the mentioned gas turbine combustor, eight pieces of the main burners 101 are disposed in the combustor cylinder body 103 and main fuel supplied from main fuel nozzles and combustion air are mixed to form a pre-mixture, which is burned in the combustor cylinder body 103 with a pilot of the pilot fuel supplied from the pilot fuel nozzle 102. The combustion air flows on the outer periphery of the combustor cylinder body 103 and turns 180° at the air inflow portion 105 to enter the combustor cylinder body 103. In the present gas turbine combustor, as shown in Fig. 1(a), the rectifier 106 is disposed at the inlet of the combustor cylinder body 103, thereby the combustion air, flowing on the outer periphery of the combustor cylinder body 103 and turning 180° at the air inflow portion 105 to enter the combustor cylinder body 103, is rectified, so that the flow velocity of the combustion air in the combustor 103 is made uniform substantially. The rectifier 106, as shown in Fig. 1(b), is of a shape having an opening of doughnut-shape so as to close a central portion of the combustor cylinder body 103, thus the combustion air flowing into the main burners 101 and the pilot air swirler 104, respectively, becomes substantially uniform in the flow rate in the combustor cylinder body 103, so that the flow velocity of the combustion air becomes nearly equal in the entire area within the combustor cylinder body 103. It is to be noted that, as shown in Fig. 1(d), in place of the rectifier 106 having the doughnut-shape opening, such a rectifier 108 may be provided as having eight pieces of round hole-shape openings 107 to position upstream on central axes of the respective main burners 101. By employing such shape of the rectifier 106 or 108, a rectifier having a lower pressure loss and a larger rectifying effect can be obtained. While the combustion air turns 180° at the air inflow portion 105 to enter the combustor cylinder body 103, there is provided on the upstream side of the main burners 101 and the pilot air nozzle 102 the rectifier 106 having the doughnut-shape opening or the rectifier 108 having the round hole-shape openings to correspond to the number of respective position of the main burners 101, thereby the combustion air is suppressed to flow at the central portion of the combustor cylinder body 103 and flows through the opening or openings. Hence, the pressure loss of the combustion air flow at the central portion increases, so that the flow rate of the combustion air flowing into the main burners 101 and that flowing into the pilot air swirler 104 become nearly equal to each other and the flow velocity of the combustion air becomes uniform in the entire area of the combustor cylinder body 103. Thus, the flow rate of the combustion air flowing into the pilot air swirler 104 is reduced and the flow velocity distribution of the combustion air at a cross section C-C of Fig. 1(a) in the combustor cylinder body 103 becomes uniform as shown in Fig. 1(c). While either of said rectifiers is of a simple structure having a high rectifying effect and an optimum rectifying effect can be selected by the size of the opening and the size of the portion closing the central portion of the combustor, the rectifier 108 having the round hole-shape openings to correspond to the number and respective position of the main burners 101 has a higher rectifying effect, as compared with the rectifier 106 having the doughnut-shape opening, in the rectifying effect to induce the combustion air into the main burners 101. In the gas turbine combustor according to the present invention, there is provided the rectifier 106 or 108 on the upstream side of the main burners 101 and the pilot air nozzle 102, thereby the combustion air flowing on the outer periphery of the combustor cylinder body 103 and turning 180° at the air inflow portion 105 is rectified before entering the combustor cylinder body 103, so that the flow velocity distribution of the combustion air in the combustor 103 cylinder body is made uniform. Thus, the flow rate of the combustion air in the main burners 101 is made uniform and concentration of the pre-mixture of the main fuel and the combustion air becomes uniform. Hence, NO x amount generated from the main burners 101 in the combustion becomes nearly zero and the combustion range within which a stable combust ion is maintained in the combustor cylinder body 103 becomes enlarged.

Claims: A gas turbine combustor comprising: a combustor cylinder body (103) having an axial center axis; an air inflow portion (105) upstream of an inlet of said combustor cylinder body (103) for turning a combustion air flow flowing on the outside of said combustor cylinder body (103) to enter said inlet of said combustor cylinder body (103); a pilot fuel nozzle (102) positioned in said combustor cylinder body (103) downstream of said inlet thereof and aligned with the center axis thereof; a pilot air swirler (104) surrounding said pilot fuel nozzle (102) and disposed for supplying combustion air towards said pilot fuel nozzle (102); a plurality of axially extending main burners (101) disposed within said combustor cylinder body (103) downstream of said inlet thereof so as to surround said pilot air swirler (104); and a rectifier (106;108) disposed at said inlet of said combustor cylinder body (103), said rectifier (106;108) having a closed central portion and an opening portion surrounding said closed central portion for suppressing flow of combustion air into the central portion of said inlet of said combustor cylinder body (103), thereby creating nearly equal flow rate of combustion air downstream of said inlet into said pilot air swirler (104) and into said main burners (101) and a uniform flow velocity distribution of the combustion air at a cross section (C-C) of said combustor cylinder body (103) downstream of said pilot fuel nozzle (102) and said main burners (101). The gas turbine combustor as claimed in Claim 1, wherein said opening portion of said rectifier (106) surrounding said closed central portion thereof is an annular opening. The gas turbine combustor as claimed in claim 1, wherein said opening portion of said rectifier (106) surrounding said closed central portion thereof comprises plural openings, each formed in a round hole shape corresponding to said plurality of main burners (101) so as to be respectively aligned with central axes of said main burners (101).

Inventors: HARUTA HIDEKI, MANDAI SHIGEMI, OHTA MASATAKA, TANIMURA SATOSHI, HARUTA, HIDEKI, MANDAI, SHIGEMI, OHTA, MASATAKA, TANIMURA, SATOSHI, Haruta, Hideki Mitsubishi Heavy Industries Ltd., Mandai, Shigemi Mitsubishi Heavy Industries Ltd., Ohta, Masataka, Mitsubishi Heavy Industries Ltd., Tanimura, Satoshi Mitsubishi Heavy Industries Ltd.
Applicants: MITSUBISHI HEAVY IND LTD, MITSUBISHI HEAVY INDUSTRIES, LTD.
Application year: 1998
Main classification: F23R3
IPC codes: F23R3, F23D23