A cooling and heating system between gas turbines
A heat recovery system and gas turbine technology, which is applied to gas turbine devices, mechanical equipment, jet propulsion devices, etc., to achieve the effects of improving combustion efficiency, increasing thrust-to-weight ratio, and increasing intake air temperature
Active Publication Date: 2017-04-19
AECC SHENYANG ENGINE RES INST
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Problems solved by technology
[0003] The purpose of the present invention is to provide a cooling and heat recovery system between gas turbines to solve or at least alleviate at least one problem existing in the technical background
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[0016] In order to make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below in conjunction with the drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, embodiments of the invention. The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below ...
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The invention discloses an intercooling and backheating system of a gas turbine. The intercooling and backheating system of the gas turbine comprises intercooling heat pipes and backheating heat pipes. One end of each intercooling heat pipe is mounted on a corresponding existing guide vane, and the other end of each intercooling heat pipe stretches into an outer duct. The heat of gas in a gas compressor is transmitted to low-temperature gas flow in the outer duct through the intrecooling heat pipes. An inlet of each backheating heat pipe is formed in a jet nozzle of an engine, an outlet of each backheating heat pipe is formed in an inlet of a combustion chamber, and the backheating heat pipes absorb the heat on the jet nozzle of the engine and transmit the heat to the inlet of the combustion chamber. The intercooling and backheating system has the beneficial effects that the heat of the gas in the gas compressor is transmitted to the low-temperature gas in the outer duct through the intercooling heat pipes, an intercooling function is achieved, compression power is saved, the thrust of the engine is increased, and the thrust-weight ratio is increased. The backheating heat pipes absorb the heat on the jet nozzle of the engine and transmit the heat to the inlet of the combustion chamber, so that the gas intake temperature of the combustion chamber is improved, and the combustion efficiency can be improved.
Description
technical field [0001] The invention relates to the technical field of cooling and heating between gas turbines, in particular to a cooling and heating system between gas turbines. Background technique [0002] A gas turbine is a typical heat engine. The most direct way to improve its efficiency is to increase the temperature before the turbine. However, the existing material level and cooling methods restrict the improvement of the thrust-to-weight ratio of the engine to a certain extent. The cooling of hot-end components such as turbine disks and blades is increasingly Difficult, when the temperature in front of the turbine is increased to a certain level, the hot-end parts cannot achieve the predetermined cooling effect, and the result may directly lead to damage to the hot-end parts, which will have a great impact on the performance and reliability of the engine; at the same time, between applications Gas turbines with high-performance new concept cycles such as cold rec...
Claims
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IPC IPC(8): F02C6/02F02C7/08
CPCF02C6/02F02C7/08
Inventor 李孝堂沈毅于霄吕多李洪莲赵孟姜楠夏梦
Owner AECC SHENYANG ENGINE RES INST