32results about How to "Reduce air conditioning" patented technology

An air conditioner includes an air conditioning case for defining an air passage through which air flows into a vehicle compartment, a functional member located in the air conditioning case for performing air conditioning of the vehicle compartment, an outside wall member arranged outside a side wall of the air conditioning case to form a clearance with the side wall, and a coupling part through which the outside wall member is integrated with the side wall. In this air conditioner, the outside wall member is located across approximately a projected line of a central line of the functional member extending in a longitudinal direction of the functional member, projected onto the side wall. Therefore, a vibration of the air conditioning case can be reduced, and a noise generation can be effectively restricted.

In a vehicle air conditioner, a blower case for accommodating a blower is connected to an air conditioning case for accommodating an evaporator and the like by a connection duct made of a vibration-absorption material. Therefore, a vibration, transmitted from the blower case to the air conditioning case, can be effectively absorbed by the connection duct, thereby reducing the vibration transmitted from the air conditioning case to a steering wheel unit through a supporting member.

Versions of the disclosure relate to multilayer flats for germinating seeds and growing plants in aeroponic or hydroponic farming. The multilayer structure can include a soilless growth medium sandwiched between a support layer and a light barrier layer. The support layer includes openings that allow plant roots to be sprayed with a nutrient solution and the light barrier layer includes openings that allow plants to develop while limiting the growth of harmful algae on the soilless growth medium.

A refrigerator has a storage compartment (3) for cooling and storing articles, a cooler (5) for generating cool air, a discharge passage (20) allowing the cool air generated by the cooler (5) to flow along the rear surface of the storage compartment (3) and having a discharge opening (20c) for discharging the cool air, a return passage (23) placed parallel to the discharge passage (20), having return openings (23a, 23b) into which the cool air flows from the storage compartment (3), and allowing the cool air flowing from the return ports (23a, 23b) to return to the cooler (5), and a member (27) formed of a good thermal conductor disposed on those sides of the discharge passage (20) and the return passage (23) which face the storage compartment (3). The discharge passage (20) and the return passage (23) are merged together on the downstream side of the return ports (23a, 23b).

The invention discloses a turbine motor of gas turbine; the turbine motor comprises a casing, a turbine motor entrance, a turbine motor exit, a turbine rotor, four-level fixed blades, and four-level movable blades. The turbine rotor comprises four impeller disks and three intermediate disks; the four impeller disks and the three intermediate disks are alternately arranged along an axial direction, and are connected together via a group of pull rods. The fixed blades are mounted on the fixed casing, and an impingement cooling sleeve is arranged therein, film holes are arranged on the surface thereof, and a convection cooling channel is arranged on the trailing edge thereof. The movable blades are mounted on one side of the rotor and revolve together with the rotor, wherein three levels are hollow structures, a double-snakelike cooling channel and multiple groups of herringbone fins are arranged therein. The fixed blades and the movable blades are alternately arranged in the axial direction of the rotor, and form a gas combustion channel therein. When the gas turbine is running, the turbine motor is able to effectively change the thermal energy of the high-temperature gas into the mechanical energy for rotating the rotor, and ensure the safety of the mechanical movement by sufficient and reasonable cooling.

The invention discloses a double-layer wall outer circle structure of a gas turbine, and belongs to a gas turbine structure. The double-layer wall outer circle structure of the gas turbine comprises an annular impact wall and blades. The impact wall comprises an outer wall body and an inner wall body. A plurality of impact holes are uniformly formed in the outer wall body. Lateral wall bodies are arranged at the two ends of the outer wall body. Supporting edges are arranged under the lateral wall bodies, and the inner wall body is located on the supporting edges. A plurality of air film holes are uniformly formed in the inner wall body. The inner wall body is connected with the outer wall body through a connecting mechanism. Under the condition that the gaps between blade tips and the outer circle inner wall body keep unchanged, the relative movement speed of the blade tips and the inner wall body is lowered through rotation of the inner wall body, and the pneumatic loss caused by relative movement is lowered by 5-10%. Due to rotation of the inner wall body, the speed of leaking fuel gas in the blade tip gaps and near the inner wall body is lowered, and the density-flow ratio between cold air sprayed by the air film holes and the leaking fuel gas in the gaps is improved, which means that the needed cold air amount is reduced in order to reach a certain cooling effect.

The invention discloses a method for designing the inlet guide vane profile of a gas turbine. The isentropic Mach number distribution and characteristic parameters of the inlet guide vane profile surface are acquired through simulation, and the low-load area and inlet attack of the inlet guide vane profile surface are obtained. Angle; cut off the low load area of ​​the leading edge of the inlet guide vane by cutting off the front edge to build a high load inlet guide vane, and increase the inlet angle of attack of the inlet guide vane to increase the inlet guide vane In order to keep the axial installation space of the blade in the aero-engine unchanged, the inlet guide vane profile is enlarged and the parameters are reconstructed, so that the distribution of aerodynamic parameters on the surface of the inlet guide vane is reasonable, the aerodynamic loss is small, and the inlet After the guide vane is enlarged, the blade grid pitch of the turbine is enlarged correspondingly, and the number of blades of the turbine is correspondingly reduced in proportion, thereby reducing the amount of cold air used for the inlet guide vane and reducing the manufacturing cost.