Country Customer Name Site Name USA Specific Reports Task Risk Assessment CSA/Invoice/Work Order Numbers Borescope Inspection YES N/A.

Transcription

1 Country Customer Name Site Name US Specific Reports Task Risk ssessment CS/Invoice/Work Order Numbers orescope Inspection YES N/ orescope Completed y Package S/N Hours Starts S/N orescope Date PD Number Customer Tag Report Date 4/20/11 N/ 4/20/11 Engine Hours Gas Liquid Total Starts Next Overhaul N/ N/ orescope Completed: efore fter Offline Compressor Wash

2 D 3 rd Stage Nozzle 3 rd Stage lades 0 Stage VGV 1 st Stage VGV 2 nd Stage VGV ir Inlet Duct ir Inlet Screen Compressor Inlet GV 0 Stage lades 0 Stage Compressor GV C orescope Ports 2 nd Stage Nozzle 2 nd Stage lages RG Inspection Port Pinion & Star Gear Star Gear 2 nd stage ccessory Gear Low Speed rg 11 th Stage Compressor lades Compressor Exit GV s Combustor Interior Torch Tube 1 st Stage Turbine Nozzle 1 st Stage Turbine lades

3 ir Inlet a) Potential FOD b) Cracks, damaged mesh Inlet Guide Vanes and size b) Excess of pitting. ffected area

4 0 Stage Compressor lades and size. b) Excessive pitting. ffected area. d) Tip rub. Gap width and metal curling. 0 Stage Compressor Guide Vanes and size. b) Excessive pitting. ffected area.p 11 Stage Compressor Guide Vanes and size. b) Excessive pitting. ffected area. Moderate

5 11 Stage Compressor lades and size. b) Excessive pitting. ffected area. Moderate

6 s a) Pilot Center body erosion b) hole contamination or blockage Slight. c) Cracks. Quantity and size s a) Pilot Centerbody erosion b) hole contamination or blockage c) Cracks. Quantity and size d) Liquid only: broken main fuel spokes Combustor Interior Quantity and size b) Thermal Erosion c) Hot spots d) uckling or warpage

7 1 st Stage Turbine Nozzle: - Leading edge - irfoil surface - Trailing edge Quantity, length, and orientation. b) Thermal erosion. Depth and affected area. Slight c) F.O.D. ffected area 1 st Stage Turbine lades: - Leading edge - irfoil surface - Trailing edge - lade Tip Quantity, length, and orientation. b) Thermal erosion. Depth and affected area. Slight c) F.O.D. ffected area d) Tip rub. Gap width.

8 oroscope Port C 2 nd Stage Turbine Nozzle: - Leading edge - irfoil surface - Trailing edge Quantity, length, and orientation. b) Cracks. c) Thermal erosion. Depth and affected area. Slight ccess T5 Port D 3 rd Stage Turbine Nozzle: - Leading edge - irfoil surface - Trailing edge Quantity, length, and orientation. b) Cracks. c) Thermal erosion. Depth and affected area. Slight

9 orescope Inspection of Gas Turbine Engine General Review The gas turbine borescope inspection is an internal inspection performed by a trained specialist who assesses the condition of the gas turbine from the air inlet through to the exhaust, using an instrument specifically designed to examine the gas path via the access ports positioned along the engine. These inspections are one of the primary diagnostic methods for maintaining turbo-machinery. oth rigid and flexible fiberscopes are used in conjunction with especially formed guide tubes to inspect the internal stationary and rotating components and to detect early signs of wear or impending failure. The major benefits of the inspection include equipment condition awareness and effective scheduling of any necessary maintenance interventions. In addition, greater reliability / longevity can be achieved through internal inspections, as well as reducing the potential of severe equipment damage. The operating gas turbine engine by design is exposed to high temperatures and rotates at high speeds. Internal inspections are thus necessary to determine if wear or thermal erosion is evident. In addition, these inspections will quantify if any foreign object damage (FOD) or corrosion has occurred, as well as assessing internal components for thermal deterioration, cracking or distortion. Though every effort is made to examine all accessible parts of the engine, there are parts of the engine that are not accessible to a borescope inspection. Therefore, a borescope inspection should not be considered to be an exhaustive evaluation of an engine s health. For example, corrosion of the under platform portion of a turbine blade cannot be seen in a borescope inspection. Thus, just because it was not seen in a borescope inspection doesn t mean it cannot exist.