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Aircraft gas turbine

An aviation gas turbine and compressed air technology, which is applied in gas turbine installations, air transportation, cooling of turbine/propulsion installations, etc., can solve the problems of reduced efficiency and difficult maintenance, and achieve the effect of ensuring clearance

Active Publication Date: 2012-09-19
MITSUBICHI HEAVY IND AERO ENGINES LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Therefore, it is difficult to maintain the gap between the front end of the rotor blade and the inner surface of the casing at an appropriate amount, and the efficiency is reduced.

Method used

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  • Aircraft gas turbine
  • Aircraft gas turbine

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0035] figure 1 is a schematic configuration diagram showing an aviation gas turbine according to Embodiment 1 of the present invention, figure 2 It is a schematic diagram of the main part of the turbine of the aviation gas turbine of Embodiment 1, image 3 It is a cross-sectional view of the main part of the casing thick-walled part of the aviation gas turbine of the first embodiment.

[0036] Such as figure 1 As shown, the aviation gas turbine of Embodiment 1 has a fan casing 11 and a body casing 12, a fan 13 is accommodated in the fan casing 11, a compressor 14, a combustor 15 and a turbine 16 are accommodated in the body casing 12 .

[0037] In the fan 13 , a plurality of fan blades 22 are attached to the outer peripheral portion of the rotating shaft 21 . The compressor 14 has a low-pressure compressor 23 and a high-pressure compressor 24 . The combustors 15 are located on the downstream side of the compressor 14 and are arranged in plural in the circumferential dir...

Embodiment 2

[0058] Figure 4 It is a schematic diagram showing the thick-walled part of the casing of the aviation gas turbine according to Embodiment 2 of the present invention. Members having the same functions as those described in the above-mentioned embodiments are assigned the same symbols and redundant descriptions are omitted.

[0059] Such as Figure 4 As shown, in the aviation gas turbine of Embodiment 2, the body casing 12 is provided with a thick-walled portion 52 corresponding to the outer peripheral side of the moving blade, so that this portion becomes a reinforced closed structure. In addition, the thick portion 52 is provided with a plurality of cooling passages 61 for cooling the thick portion 52 by circulating the compressed air compressed by the compressor. The plurality of cooling passages 61 are meandering.

[0060] That is, a cooling passage 61 is composed of three paths: an inlet passage 62 with an opening at the suction portion 54, an outlet passage 64 at the o...

Embodiment 3

[0065] Figure 5 It is a schematic diagram showing the thick wall portion of the casing of the aviation gas turbine according to Embodiment 3 of the present invention. Members having the same functions as those described in the above-mentioned embodiments are assigned the same symbols and redundant descriptions are omitted.

[0066] Such as Figure 5 As shown, in the aviation gas turbine of Embodiment 3, the body casing 12 is provided with a thick-walled portion 52 corresponding to the outer peripheral side of the moving blade, so that this portion becomes a reinforced closed structure. In addition, the thick portion 52 is provided with a plurality of cooling passages 71 for cooling the thick portion 52 by circulating the compressed air compressed by the compressor.

[0067] This cooling passage 71 includes: a cavity 72 that ensures a predetermined amount of space in the thick wall portion 52; The chamber 72 communicates with a plurality of outlet passages 74 whose other en...

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PUM

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Abstract

Disclosed is an aircraft gas turbine comprising a compressor (14), a combustor (15) and a turbine (16) housed in a cylindrical main body casing (12). The main body casing (12) is provided with a thick walled section (52) on its peripheral edge on the side of the moving blades (34), where compressed air compressed by the compressor (14) is circulated inside the thick walled section (52) which is provided with a cooling passage (53) for cooling and also an exhaust passage (55) which discharges the compressed air circulated in the cooling passage (53) through the combustion gas passage A. Accordingly, construction is simplified and loss of efficiency is prevented, while the structural strength of the thick walled sections is ensured by appropriate cooling provided by the thick walled sections in the casing, and efficient containment properties as well as sufficient clearance for the moving blades is also ensured.

Description

technical field [0001] The present invention relates to an aeronautical gas turbine having a compressor, a combustor and a turbine arrangement housed within a housing. Background technique [0002] Gas turbines are used as engines for aircraft such as helicopters and jet aircraft. The aviation gas turbine is composed of a compressor, a combustor and a turbine. The air entering from the air inlet is compressed by the compressor to become high-temperature and high-pressure compressed air. The combustor supplies fuel to the compressed air and burns it. gas to drive the turbine. In the case of a helicopter it is the driving force of the turbine that spins the rotor, in the case of a jet it is the energy of the exhaust that gets the thrust. [0003] The turbine constituting the aviation gas turbine has a plurality of stationary blades and movable blades alternately arranged in the casing, and the rotating blades are driven by gas to obtain rotational driving force and drive the...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F01D25/24F01D25/12F01D25/26F02C7/00F02C7/18
CPCF01D25/14F01D11/24F05D2220/323F05D2250/185F05B2260/205F02C7/18Y02T50/676F05D2260/205F05B2220/303Y02T50/60F05D2240/11
Inventor 北村刚真崎信一郎
Owner MITSUBICHI HEAVY IND AERO ENGINES LTD