OT-2014-30009_DID_--_Propulsion_Characteristics_Summary - FINAL.pdf

OT-2014-30009

DATA ITEM DESCRIPTION

Title: Propulsion Characteristics Summary

Number: OT-2014-30009 Approval Date: 20140129

AMSC Number: Limitation: Component Improvement Program

DTIC Applicable: GIDEP Applicable: No

Office of Primary Responsibility: AFLCMC/LP

Applicable Forms:

Use/relationship:

The Propulsion Characteristics Summary will be used to obtain detailed engine performance data and engine characteristics collected from contractors to create a single reference source of realistic and readily comparable data. This DID is for one-time use for the Component Improvement Program (CIP) contracts.

Requirements:

1. Reference documents. Any references to specifications throughout this document shall be understood to refer to the latest approved version of the engine Prime Item Development (PID) or Prime Item Performance

(PIP) specification applicable to the engine TMS being reported on.

2. Format. The Propulsion Characteristics Summary shall be provided in the format of Figure 1, shown at the end of this DID. Terms, symbols and their definitions shall be in accordance with this DID.

3. Content. Instructions for completing each numbered item in Figure 1 are provided below. Figure 1 is not an official form; rather, it is intended to be camera-ready copy suitable for reproduction to facilitate formatting of the data suitable for the Gray Book.

2.1 - Item (1) SECURITY CLASSIFICATION -At each occurrence of (1) indicate the highest classification of the data presented on the summary. Include the special notation which identifies its status in the automatic, time-phased downgrading and declassification system, in accordance with current applicable security regulations.

2.2 - Item (2) MILITARY DESIGNATION - At each occurrence of (2) enter the official military designation.

If there is none assigned, show all other designations by which the particular engine is identified.

2.3 - Item (3) CONTRACTOR'S DESIGNATION - Enter the contractor's designation and popular name for the engine. If not applicable, enter ''None."

2.4 - Item (4) SPECIFICATION DATA - Enter the contractor's name, location (city and state), model specification number from which the data is derived (if none, indicate the source and date of data such as report number, bulletin, or progress reports), the latest date of the specification, and whether it has or has not been approved by the cognizant Government agency.

2.5 - Item (5) PICTORIAL DATA - Furnish a glossy photograph (side view) with the exhaust nozzle to the right. If no photograph is available, a linear drawing, blueprint drawing, or artist’s sketch is satisfactory.

Pictorial data may be furnished in its original form.

2.6 - Item (6) SPONSORING AGENCY - Enter name of the Government agency originally sponsoring the project, i.e., ARMY, NAVY, USAF, etc. If not Government sponsored, indicate responsible contractor.

2.7 - Item (7) FEATURES - Provide a general description as well as special data relative to cooling, liquid injection, afterburning, reliability, specialties, limitations, engine life expectancy, advancements and similarities to previous models, etc., as applicable.

2.8 - Item (8) AVAILABILITY

a. Program Initiated. (Enter month and year program was initiated.)

b. Development Contract Award. (Enter month and year of contract award. If not applicable, insert ''None.")

c. Engine Mock-Up Inspection. (Enter month and year scheduled for official completion. If not applicable, insert ''None.")

d. Experimental Engine. (Enter month and year scheduled for initial operation as a complete assembly or alternatively known as the first engine to test. If not applicable, insert ''None." An experimental engine is basically defined as an engine that has not completed the Preliminary Flight

Rating Test).

e. Mock-Up for Vehicle. (Enter month and year scheduled for official completion. If not applicable, insert ''None.")

f. Installation Engine. (Enter month and year that first flight engine could be or is made available for prototype vehicle application. If not applicable, insert ''None.")

g. Preliminary Flight Rating Test/Initial Flight Release. (Enter month and year scheduled for official completion. If not applicable, insert ''None.")

h. Qualification Test/Initial Service Release. (Enter month and year scheduled for official completion. If not applicable, insert ''None." If demonstration or FAA Certification only is required, indicate month and year scheduled and insert below the Qualification Test line.)

2.9 - Item (9) CONTRACTUAL -If demonstration, experimental, or research engine, provide all contract numbers, contract coverage, and total contract cost. If production or service test engine, provide all contract numbers, quantities per contract, and unit cost. No data is required for post-production contracts.

2.10 - Item (10) STATUS -Provide current status, i.e., in design stage, undergoing component development, first firing date, In production, production completed in (month-year), currently undergoing production buildup, number of engines produced to date, etc., as applicable. Provide information required to fully portray the current status, stage of development, and availability.

2.11 - Item (11) GENERAL - All applicable performance and characteristics parameters are based on sea level static, standard day conditions.

a. (For single rotor compressor,) Compressor: _____________________________ (Provide type, single rotor, number of stages, includes _______ fan stages, variable geometry, etc.)

(For dual rotor compressor,)

Compressor: _____________________________

LP Rotor: ____________________________

HP Rotor: ____________________________

(Provide compressor type, dual rotor, number of stages for each rotor (includes ____ fan stages), variable geometry, etc.)

b. (For single rotor compressor,)

Max Design Pressure Ratio/SLS:

Fan: ________________________________: 1

Overall: _____________________________: 1

(Express ratio to nearest 0.1)

(For dual rotor compressor,)

Max Design Pressure Ratio/SLS:

Fan: _________________________________: 1

LP Rotor: _____________________________: 1

HP Rotor: _____________________________: 1

Overall: _______________________________: 1

(Express ratio to nearest 0.1)

c. Bypass Airflow Ratio (Turbofan engine only): _______________ :1 (bypass airflow to HP compressor airflow; express ratio to nearest 0.1.)

d. Max Allowable Air Bleed: _______________ % (equals compressor air bleed divided by Max Rated Power compressor airflow; express to nearest 0.1 percent.)

e. Max Rated Airflow/SLS: _____________lbm/sec (at max or takeoff rated power, as applicable; express to nearest unit.)

f. Combustion Chamber: ____________________ (type, number, flow, etc.)

g. (For single rotor turbine,)

Turbine: _____________________ (type, single rotor, number of stages, variable geometry, etc.)

(For dual rotor turbine,)

Turbine: ____________________

LP Rotor: ____________________

HP Rotor: ___________________

(turbine type, dual rotor, number of stages per rotor, variable geometry, etc.)

h. Max Allowable Avg. Steady-State Temp (Combustor Exit):_______________(°F) (max temperature in operating envelope or control limit)

i. Max Allowable Avg. Steady-State Temp (Turbine Rotor Inlet):_______________(°F) (max temperature in operating envelope or control limit)

j. Max Allowable Turbine Metal Temp:_______________(°F) (max design blade temperature)

k. Turbine Cooling: ______________________ (type, i.e., air, liquid, none, etc.)

l. Max Rated Turbine Inlet Temp/SLS:_______________(°F) (temperature at max or takeoff rated power, as applicable)

m. Max Rated Turbine Rotor Inlet Temp/SLS: ):_______________(°F) (temperature at max or takeoff rated power, as applicable)

n. Exhaust Nozzle: ________________ (type, variable, convergent, divergent, two position, fixed area, exit area, etc.)

o. Regeneration: __________________ (type, location, none, etc.)

p. Max Rated Exhaust Temp/SLS: _________________(°F) (temperature at max or takeoff rated power, as applicable, at exit point.)

q. Electrical System: ___________________(voltage, cycle and max amperage requirements.)

r. Ignition: ____________________ (type, number of igniters, etc.)

s. Power Control: __________________ (type, i.e., electrical, hydro-mechanical, pneumatic, digital computer, etc.)

t. Fuel: _______________________ (list designation type and military specification for both primary and alternate fuels.)

u. Oil: _______________________ (List designation type, grade and military specification.)

v. MCP Oil Consumption: _______________________ gal/hr (at max continuous or normal rated power, as applicable; express to nearest 0.1 gal/hr.)

w. Accessory Drive Provisions: _____________________ (list number of drives provided.)

x. Thrust to Weight Ratio: _____________________________ : 1 (based on max rated power; express to nearest 0.1.)

2.12 - Item (12) SIZE & WEIGHT - Provide all data at room temperature. Show size and weight data from the engine specification. If the specification size and weight are not achieved for the engine, the current approved baseline should be shown.

a. Length, Overall _____________________________ in. (parallel to centerline axis; express to nearest 0.01 inch)

b. Diameter, Nominal _____________________________in. (perpendicular to the centerline axis; express to nearest 0.01 inch)

c. Max Radial Projection _________________________________ in. (perpendicular to the centerline axis;

express to nearest 0.01 inch)

d. Weight, Dry ____________________________ lb. (items furnished with the engine which are not engine components shall not be included; express to nearest pound.)

e. Weight, Wet _____________________________ lb. (equals the dry weight plus residual fluids after operation and drainage; express to nearest pound.)

2.13 - Item (13) UTILIZATION - Indicate the vehicle application by both nickname and military designation.

Include number of engines per application, and indicate the using service for each vehicle.

2.14 - Item (14) DATE - Enter date indicating currency of summary.

2.15 - Item (15) PERFORMANCE - Enter performance from the Performance Table(s) from the applicable engine specification. If specification performance is not achieved for the engine, the current approved performance baseline should be provided.

2.16 - Item (16) GRAPHIC PERFORMANCE - Provide thrust vs. SFC curves for selected sea level, altitude, and flight speeds. Selection should be based on engine/vehicle application requirements as well as the engine capability. The basic data is generally obtained from a performance model or engine specification. The data should be consistent with the current, approved performance baseline. Indicate the ram efficiency and model atmosphere used.

2.17 - Item (17) NOTES - Provide any additional information necessary to fully portray the engine presentation or capability.

3.0 Content. Required information shall be provided in the format above.

4. End of OT-2014-30009.

Figure 1: Summary Format (1) OT-2014-30009

Propulsion Characteristics Summary

Turbofan/Turbojet/Turboprop (2)

(3) (4)

(5)

(7) Features

(6)

(8) Availability (9) Contractual

Program Initiated:

Development Contract Award:

Engine Mock-up Inspection:

Experimental Engine:

Mock-up Vehicle:

Installation Engine Prelim Flight Rating/Initial Flight Release:

Qualification Test/Initial Service Release:

(10) Status

(11) Compressor:

LP Rotor:

HP Rotor:

Max Design Pressure Ratio/SLS Fan: : 1 LP Rotor: : 1 HP Rotor: : 1 Overall: : 1

Bypass Airflow Ratio: : 1 Max Allowable Air Bleed: % Max Rated Airflow/SLS: _lbm/sec Combustion Chamber:

Turbine:

LP Rotor:

HP Rotor:

Max Allowable Avg. Steady-State Temp (Combustor Exit) °F

General Max Allowable Avg. Steady-State Temp (Turbine

Rotor Inlet) °F Max Allowable Turbine Metal Temp______°F Turbine Cooling:

Max Rated Turb Inlet Temp/SLS: _°F Max Rated Turb Rotor Inlet Temp/SLS: _°F Exhaust Nozzle:

Regeneration:

Max Rated Exhaust Temp/SLS: °F Electrical System:

Ignition:

Power Control: _ Fuel: ______________(alt)________________ Oil:

MCP Oil Consumption _gal/hr Accessory Drive Provisions Thrust-to-Weight Ratio: ________________: 1

(12) Size & Weight (13) Utilization Length, Overall in.

Diameter, Nominal in.

Max Radial Projection in.

Weight, Dry _ ___ lb.

Weight, Wet _______________________ lb.

(14) (1) (2)

Figure 1: Summary Format (Continued) OT-2014-30009

(1)

Rating at Status Sea Level Conditions

Rating Thrust RPM SFC

(lbm/hr/lbf)

Turbine Gas

Temp (°F)

Airflow

(lbm/sec)

Altitude Ratings—US Standard Atmosphere

Rating Altitude (ft) Mach Thrust

(lbf)

SFC

(lbm/hr/lbf)

Turbine Gas

Temp (°F)

Airflow

(lbm/sec)

Guaranteed Operating Limits Absolute Altitude ft. Max Starting Altitude, Ground ft.

Max Mach Number Max Starting Altitude, Restart ft.

(16)

Thrust (lbf)

(17) Notes

Dfg

SF

C lb m /h r/ lb f)

Performance

X Guaranteed Range

(2) (1) (14)

(15)