Abstract: A heat exchange wall include a base plate; a plurality of first protrusions distributedly provided on a surface of the base plate, and a plurality of second protrusions distributedly provided on the base plate surface. The height of the second protrusion in a normal direction of the base plate is desirably less than ½ of a height of the first protrusion in the normal direction. The height of the second protrusion in the normal direction is desirably between 1/20 and ¼ of the height of the first protrusion in the normal direction. More desirably, the height of the second protrusion in the normal direction is 1/10 of the height of the first protrusion in the normal direction.

Abstract: A gas turbine system composed of a gas turbine engine and a controller. The gas turbine engine includes an annular combustor, and a turbine driven by combustion gas from the annular combustor to rotate on a longitudinal centerline axis of the gas turbine engine. The annular combustor is comprised of an outer casing, a liner disposed in the outer casing, and a plurality of dilution air regulators introducing dilution air into the liner. The plurality of dilution air regulators are circumscribed about the longitudinal centerline axis and spaced apart at substantially equal intervals. The controller controls the plurality of dilution air regulators to individually adjust dilution air flows through the plurality of dilution air regulators into the liner.

Abstract: A gas turbine combustor that controls flow rate of air flowing into a primary combustion zone for controlling a local fuel-air ratio comprises no sliding portion that is liable to cause sticking or biting of components operating in high temperature, thereby providing a simple, reliable and efficient combustor and a combustion control method thereof. The gas turbine combustor comprising a liner provided in a combustor case and a bypass duct provided in the liner and enabling a control of flow rate of air supplied into a primary combustion zone via a swirler by causing a portion of the air to pass through the bypass duct, further comprises a float, made of a magnetic substance, provided in the bypass duct so as to open and close the bypass duct by the position of movement of the float and an electromagnetic coil provided outside of the combustor case corresponding to the position of the float so as to move the float.

Abstract: A heat exchange wall include a base plate; a plurality of first protrusions distributedly provided on a surface of the base plate, and a plurality of second protrusions distributedly provided on the base plate surface. The height of the second protrusion in a normal direction of the base plate is desirably less than ½ of a height of the first protrusion in the normal direction. The height of the second protrusion in the normal direction is desirably between {fraction (1/20)} and ¼ of the height of the first protrusion in the normal direction. More desirably, the height of the second protrusion in the normal direction is {fraction (1/10)} of the height of the first protrusion in the normal direction.

Abstract: A gas turbine system is composed of a gas turbine engine, and a controller. The gas turbine engine includes an annular combustor, and a turbine driven by combustion gas from the annular combustor to rotate on a longitudinal centerline axis of the gas turbine engine. The annular combustor is comprised of an outer casing, a liner disposed in the outer casing, and a plurality of dilution air regulators introducing dilution air into the liner. The plurality of dilution air regulators are circumscribed about the longitudinal centerline axis and spaced apart at substantially equal intervals. The controller controls the plurality of dilution air regulators to individually adjust dilution air flows through the plurality of dilution air regulators into the liner.

Abstract: A gas turbine combustor that controls flow rate of air flowing into a primary combustion zone for controlling a local fuel-air ratio comprises no sliding portion that is liable to cause sticking or biting of components operating in high temperature, thereby providing a simple, reliable and efficient combustor and a combustion control method thereof. The gas turbine combustor comprising a liner provided in a combustor case and a bypass duct provided in the liner and enabling a control of flow rate of air supplied into a primary combustion zone via a swirler by causing a portion of the air to pass through the bypass duct, further comprises a float, made of a magnetic substance, provided in the bypass duct so as to open and close the bypass duct by the position of movement of the float and an electromagnetic coil provided outside of the combustor case corresponding to the position of the float so as to move the float.

Abstract: An annular type gas turbine combustor which can regulate air flow distribution without being influenced by high temperature flames and with a desired fuel-air ratio for reducing the generation of NO.sub.x etc. A slide duct (10), for regulating air flow distribution, is disposed slidably in an axial direction at a terminal end of a diffuser (1). And as the slide duct (10) is moved, air flow supplied downstream to a swirler (4) is regulated so as to obtain a desired fuel-air ratio.