Name: Preliminary Results of an Altitude-Wind-Tunnel Investigation of a Tg-100a Gas Turbine-Propeller Engine: V; Combustion-Chamber Characteristics (en Inglés)
Price: 500.59 MXN
Availability: InStock
Author: Gensenheyner, Robert M. ; Berdysz, Joseph J. ; Nasa Technical Reports Server (Ntrs)
ISBN: 9781289261436

Envío gratis

portada Preliminary Results of an Altitude-Wind-Tunnel Investigation of a Tg-100a Gas Turbine-Propeller Engine: V; Combustion-Chamber Characteristics (en Inglés)

Formato

Libro Físico

Autor

Nasa Technical Reports Server (Ntrs)

Robert M. Gensenheyner

Joseph J. Berdysz

Editorial

Bibliogov

Idioma

Inglés

N° páginas

Encuadernación

Tapa Blanda

Dimensiones

24.6 x 18.9 x 0.2 cm

Peso

0.09 kg.

ISBN13

9781289261436

Categorías

Política y gobierno

Preliminary Results of an Altitude-Wind-Tunnel Investigation of a Tg-100a Gas Turbine-Propeller Engine: V; Combustion-Chamber Characteristics (en Inglés)

Nasa Technical Reports Server (Ntrs) (Autor) · Robert M. Gensenheyner (Autor) · Joseph J. Berdysz (Autor) · Bibliogov · Tapa Blanda

Libro Nuevo

$ 500.59

$ 834.32

Ahorras: $ 333.73

40% descuento

Envío normal

Origen: Estados Unidos (Costos de importación incluídos en el precio)

Se enviará desde nuestra bodega entre el Lunes 22 de Julio y el Martes 30 de Julio.

Lo recibirás en cualquier lugar de México entre 1 y 3 días hábiles luego del envío.

Reseña del libro "Preliminary Results of an Altitude-Wind-Tunnel Investigation of a Tg-100a Gas Turbine-Propeller Engine: V; Combustion-Chamber Characteristics (en Inglés)"

An investigation to determine the performance and operational characteristics of the TG-1OOA gas turbine-propeller engine was conducted in the Cleveland altitude wind tunnel. As part of this investigation, the combustion-chamber performance was determined at pressure altitudes from 5000 to 35,000 feet, compressor-inlet rm-pressure ratios of 1.00 and 1.09, and engine speeds from 8000 to 13,000 rpm. Combustion-chamber performance is presented as a function of corrected engine speed and.correcte& horsepower. For the range of corrected engine speeds investigated, over-all total-pressure-loss ratio, cycle efficiency, ana the frac%ional loss in cycle efficiency resulting from pressure losses in the combustion chambers were unaffected by a change in altitude or compressor-inlet ram-pressure ratio. The scatter of combustion- efficiency data tended to obscure any effect of altitude or ram-pressure ratio. For the range of corrected horse-powers investigated, the total-pressure-loss ratio an& the fractional loss in cycle efficiency resulting from pressure losses in the combustion chambers decreased with an increase in corrected horsepower at a constant corrected engine speed. The combustion efficiency remained constant for the range of corrected horse-powers investigated at all corrected engine speeds.