1. Blade for gas turbine

2. Split-flow recirculating gas turbine

3. Burner for a gas turbine and method for reducing thermo-acoustic oscillations in a gas turbine

4. Gas turbine compressor cleaning units

5. Gas turbine engine fuel air mixer

6. A gas turbine engine system includes a gas turbine engine (10) having aerodynamic drag that retards movement.

7. Gas turbine, particularly an aircraft engine

8. Gas turbine aero engine afterbody assembly

9. Combustion chamber arrangement for damping thermo-acoustic oscillations, gas turbine and method of operating such a gas turbine

10. Gas turbine system having exhaust gas recirculation

11. Blade tip sealing apparatus for gas turbine

12. The present invention relates to a gas turbine.

13. Accessory mechanical drive for a gas turbine engine

14. Gas turbine engine component having vascular engineered lattice structure

15. Gas turbine engine with air-oil cooler oil tank

16. Gas turbine burner assembly equipped with a helmholtz resonator

17. Aero gas turbine engines having any of the following:

18. The gas turbine also keeps the batteries topped up.

19. In order to reduce gas turbine disk stress, an optimal material removal area is defined according to blade and/or disk geometry to maximize a balance between stress reduction on the gas turbine disk, a useful life of the gas turbine blade, and maintaining or improving the aeromechanical behavior of the gas turbine blade.

20. Closed-loop control for a gas turbine with actively stabilized compressor

21. Acoustic damping system for a combustor of a gas turbine engine

22. The invention relates to a gas turbine, especially an aircraft engine.

23. Aftermarket services for gas turbine engines, namely, overhaul repair maintenance services

24. Gas turbine engine combustor circumferential acoustic reduction using flame temperature nonuniformities

25. A premixing injector for use in gas turbine engines assists in the lean premixed injection of a gaseous fuel/air mixture into the combustor of a gas turbine.

26. Gas turbine including blade tip gap adjusting means and control method therefor

27. An accessory drive system for an aircraft gas turbine engine is disclosed.

28. The present invention relates to an airfoil (100) for a gas turbine.

29. They were the first gas turbine powered ships in the Soviet navy.

30. Gas turbine engine two degree of freedom variable bleed valve for ice extraction

31. Partial-load operation of a gas turbine with an adjustable bypass flow channel

32. Gas turbine engine with system to adjust clearance between rotating and stationary components

33. The batteries are charged on-board by a small gas turbine auxiliary propulsion unit.

34. A method for making a gas turbine engine ceramic matrix composite airfoil is disclosed.

35. Method for mounting a mixing housing in a gas turbine, and adjusting device therefor

36. The Gas Turbine Research Establishment was to indigenously develop the Kaveri engine to power the LCA .

37. 9A001 Aero gas turbine engines incorporating any of the "technologies" specified in 9E003.a., as follows:

38. specially designed to predict aero thermal, aeromechanical and combustion conditions in aero gas turbine engines; and

39. The invention relates to a device for the adjustment of guide blades of a gas turbine.

40. Non-civil certified aircraft; all aero gas turbine engines; unmanned aerial vehicles; and parts and components

41. NRC Aerospace engineers, pilots and technicians test structures and components, new materials and gas turbine engines.

42. Specially designed to predict aero thermal, aeromechanical and combustion conditions in aero gas turbine engines; and

43. As turbine-driven air compressors driven by an exhaust-gas turbine, they fall in heading 8414.

44. Method and device for operating a burner of a heat engine, especially a gas turbine plant

45. Note: 9A001.a. does not control aero gas turbine engines which meet all of the following:

46. Note 1: 9A001.a. does not control aero gas turbine engines which meet all of the following:

47. The Gas Turbine Research Establishment was entrusted with the task of designing the engine for the LCA .

48. The contract pertained to the repair, overhaul and modification of Allison T56 gas turbine engines for aircraft.

49. But not including aircraft engines, gas turbine engines for aircraft, and parts and fittings for these goods

50. Apparatus for acoustic damping and operational control of damping, cooling, and emissions in a gas turbine engine

51. 1. Specially designed to predict aero thermal, aeromechanical and combustion conditions in aero gas turbine engines; and

52. Process and tool for aligning a seal housing assembly with a casing of a gas turbine engine

53. It manufactures power turbines for electricity and heat generation, gas compressor units and marine gas-turbine units.

54. 1. being specially designed to predict aero thermal, aeromechanical and combustion conditions in aero gas turbine engines; and

55. Said drag device (33) leads a gas turbine blade on a carrier arm (41) through the abrasive medium (27).

56. The invention relates to a device for adjusting guide blades of a turbo drive gear, especially a gas turbine.

57. Wärtsilä’s Competitors in power generation comprise equipment manufacturers of internal combustion engine and gas turbine technologies

58. Vapour Aluminising or out-of-pack Aluminising is a major production technique for producing aluminide coatings on gas turbine parts

59. Centrifugal compressors are used in small gas turbine engines or as the final compression stage of medium-sized gas turbines.

60. The burner permits the reduction of thermo-acoustic oscillations in a combustion chamber on a gas turbine in an alternative way.

61. Method for optimizing the contact surfaces of shroud segments, which abut against one another, of adjacent blades of a gas turbine

62. In modern gas-turbine helicopters, much of this work has been reduced by the introduction of an engine speed governing system.

63. Almost all of the modern gas turbine engines use Annular combustors; likewise, most combustor research and development focuses on improving this type

64. This leads to violent oscillations known as 'thermo-acoustic instabilities’, resulting in profound damage to a gas turbine that is expensive to replace.

65. The method comprises passing the residual gases leaving the absorption tower, through a two-stage combination before introduction into the residual gas turbine.

66. In a third step, the calculated fault probabilities are displayed and transmitted to a planning system for scheduling of gas turbine operation or maintenance actions.

67. The invention relates to a gas turbine group (1) comprising means (3) arranged in a suction channel (2), for cooling an intake air flow (21).

68. Aerospace and industrial gas turbine components such as blades, vanes, casings, and discs will be coated by PST’s Aluminising, platinum Aluminising, slurry, and thermal spray processes

69. Theoretical modelling predictions of the aero thermal, aeromechanical and combustion conditions, which have been validated with actual aero gas turbine engine (experimental or production) performance data.

70. Energy Developments, operator of this project, also is demonstrating a lean fuel gas turbine which may use ventilation air methane for much of its fuel needs

71. Energy Developments, operator of this project, also is demonstrating a lean fuel gas turbine which may use ventilation air methane for much of its fuel needs.

72. The invention relates to an evaporative cooler for mounting inside stationary installed or mobile installations, in particular, inside intake air channels of gas turbine power plants.

73. 2. Theoretical modelling predictions of the aero thermal, aeromechanical and combustion conditions, which have been validated with actual aero gas turbine engine (experimental or production) performance data.

74. The no machining directional solidification hollow turbine blades, hollow guide vans and complex structure parts used in aero engine and gas turbine made by vacuum precision investment casting.

75. The invention relates to a method for producing a rotor or stator blade (1a) of a gas turbine, in particular an aircraft gas turbine (2), comprising forming a airfoil (8a) made of at least one first material and attaching a blade root (4a) made of at least one second material to the airfoil (8a) by means of a thermal spraying method.

76. PROPULSION SYSTEMS, SPACE VEHICLES, AND RELATED EQUIPMENT 9A EQUIPMENT, ASSEMBLIES AND COMPONENTS 9A001 Aero gas turbine engines incorporating any of the technologies specified in 9E003.a, as follows:

77. To improve the reliability of gas turbines for power generation was the aim of the EU-funded 'Limit cycles of thermo-acoustic oscillations in gas turbine combustors' (LIMOUSINE) project.

78. * Power sector: Recognising the existing capabilities of BHEL in manufacturing gas turbine units, the Iraqi side agreed to include BHEL as a qualified Equipment Manufacturer for its power sector.

79. The ship will be powered by four gas-turbine engines and will have a range of 8,000 nautical miles (15,000 kilometres), carrying 160 officers, 1,400 sailors, and 40 aircraft.

80. Cogeneration plants are energy efficient and can be attractive options for reduction of operating costs, especially where the gas turbine exhaust can be used for heating or steam generation