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Gas turbine engine with low stage count low pressure turbine

A technology of gas turbine and low pressure turbine, which is applied to gas turbine devices, gas turbine power plants, engine components, etc., and can solve problems such as affecting engine performance, increasing fuel combustion, and increasing clearance.

Active Publication Date: 2014-07-30
UNITED TECH CORP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This twisting results in increased clearance between the static case and the rotating blade tips, which adversely affects engine performance and increases fuel burn

Method used

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  • Gas turbine engine with low stage count low pressure turbine
  • Gas turbine engine with low stage count low pressure turbine
  • Gas turbine engine with low stage count low pressure turbine

Examples

Experimental program
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Embodiment Construction

[0037] Figure 1A A schematic view of the overall partial part of the gas turbofan engine 10 is shown, as is the usual case of an aircraft designed for subsonic operation, the engine 10 is suspended from the engine pylon 12 in the engine nacelle assembly N.

[0038] The turbofan engine 10 includes a core engine in a core nacelle C that houses a low-pressure reel 14 and a high-pressure reel 24. The low-pressure reel 14 includes a low-pressure compressor 16 and a low-pressure turbine 18. The low pressure reel 14 drives the fan section 20 connected to the low pressure reel 14 directly or through a gear train 25.

[0039] The high-pressure reel 24 includes a high-pressure compressor 26 and a high-pressure turbine 28. The combustion chamber 30 is provided between the high-pressure compressor 26 and the high-pressure turbine 28. The low and high pressure reels 14, 24 rotate around the engine rotation axis A.

[0040] The engine 10 in the non-limiting embodiment is a high-bypass gear fram...

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PUM

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Abstract

A gas turbine engine according to an exemplary aspect of the present disclosure includes a gear train defined along an engine centeriine axis, and a spool along said engine centeriine axis which drives the gear train, the spool includes a low stage count low pressure turbine. In a further non-limiting embodiment of any of the foregoing gas turbine engine embodiments, the low stage count may include three to six (3-6) stages. Additionally or alternatively, the low stage count may include three (3) stages. Additionally or alternatively, the low stage count may include five (5) or six (6) stages.

Description

[0001] Cross references to related applications [0002] This disclosure is a partial continuation application of US Patent Application Serial No. 12 / 131876 filed on June 2, 2008. Technical field [0003] The present invention relates to a gas turbine engine, and more particularly to an engine mounting structure for mounting a turbofan type gas turbine engine to an aircraft outer pylon. Background technique [0004] The gas turbine engine may be installed at various points on the aircraft (for example, an external pylon formed integrally with the aircraft structure). The engine mounting structure ensures load transmission between the engine and the aircraft structure. The load usually includes the weight of the engine, thrust, aerodynamic side load and rotational torque about the engine axis. The engine installation structure must also reduce the deformation of the engine during different flight periods and the dimensional changes due to thermal expansion and contraction. [0005] ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64D27/10B64D27/40
CPCF02K3/075F01D25/162F02C3/107F02C7/20F02K3/06F05D2260/4031F05D2260/40311B64D27/402B64D27/404B64D27/40F02K1/06
Inventor 加布里埃尔·L·萨丘布赖恩·D·梅里克里斯多佛·M·戴伊史蒂文·B·约翰逊弗雷德里克·M·施瓦兹
Owner UNITED TECH CORP