Gas turbine engine

In 1791 Engs. inventor J. Barber for the first time proposed the idea of creation GTD - GAS-TURBINE ENGINE with the gas generator, the air pump, the combustion chamber and the gas turbine. Russian. Eng.. P. D. Kuz'minskiy into 1892 developed project, and into 1900 built GTD - GAS-TURBINE ENGINE with the combustion of fuel at a constant pressure, intended for the small launch. In this GTD - GAS-TURBINE ENGINE multistage gas turbine was used. Tests not were completed because of death Of kuz'minskogo. In 19go-04 Ger. eng. f. Stolz it attempted to create GTD - GAS-TURBINE ENGINE, but it is unsuccessful. In 1906 French of eng. r. of Are- mango and Sh. lemal' built GTD - GAS-TURBINE ENGINE, which worked on the kerosene, with the combustion of fuel at a constant pressure, but because of low efficiency it did not obtain industr. application. In 1906 Russ. eng. v. V. kara-vodin -vodin designed, and into 1908 built compressorless GTD - GAS-TURBINE ENGINE with 4 cameras of intermittent combustion and gas turbine, which with 10 000 r/min developed power 1,2 kW (1,6 l. s.). In 1908 according to the project of Ger. eng. X Khol'tsvarta was built WITH GTD - GAS-TURBINE ENGINE of intermittent combustion. To 1933 efficiency GTD - GAS-TURBINE ENGINE with the intermittent combustion it composed 24%; however, they did not find a wide industr. use. In Russia in 1909 eng. N. V. Gerasim obtained patent on GTD - GAS-TURBINE ENGINE, which was used by them for creating the reactive thrust (turbojet GTD - GAS-TURBINE ENGINE),; in 1913 M. n. nikol'skoys was designed GTD - GAS-TURBINE ENGINE with a power of 120 kW (160 ls.) with the three-stage gas turbine; in 1923 V. i. bazarovs it proposed the diagram GTD - GAS-TURBINE ENGINE, close to the schematics of contemporary turboprop engines; in 1930 v. V. uvarov with N. r. briling's participation designed, and into 1936 built GTD - GAS-TURBINE ENGINE with the centrifugal compressor. In the 30's the large contribution to the creation by avn.. GTD - GAS-TURBINE ENGINE introduced the Sov. designer A. m. lyul'k (now Acad.. AS USSR), Eng, inventor F. uittl, Ger. eng. l. Franz et al. In 1939 in Switzerland it was built and tested BY GTD - GAS-TURBINE ENGINE with a power of 4000 salmon (5400 l. s.). Slovakian scientific A. Stodola was its creator. In 1939 in Kharkov, in the laboratory, rukovodimoy V. m. makovskiy, prepared GTD - GAS-TURBINE ENGINE with a power of 736 kW (1000 l. s.). The gas, obtained with the subterranean gasification of coal, is used as the fuel. The tests of this GTD - GAS-TURBINE ENGINE in Gorlovke were interrupted by World War II. The large contribution to development and improvement GTD - GAS-TURBINE ENGINE introduced Sov. scientists the designers: A. g. Ivchenko, In. 4. Klimov, n. d. Kuznetsov, I. i. kulagin, T. m. mel'kumov, A. A. Miku- lin, B. S. stechkin, S. K. tumanskiy, 4. i. shnee, L. A. wubenko-Wubin -Wubin et al. abroad into the 40's at creation GTD - GAS-TURBINE ENGINE worked firm "cadet", "BMV" (Germany), "bristol Of sidli", "Rolls-Royce" (Great Britain), by "General Electric" and "General motor" (USA), "rato" (France) and other.

The greatest industr. application obtained GTD - GAS-TURBINE ENGINE with the continuous combustion of fuel at the constant pressure, in such a GTD - GAS-TURBINE ENGINE (Fig. 1) air from the compressor compressed by atm enters combustion chamber, there it will be given with fuel-, which, burning, nagrevayet air; then in the gas turbine energy of gaseous combustion products is converted into the mech. work, whose the large part is expended on the air compression in the compressor. The remaining part of the work is transferred on the given aggregate. The work, consumed by this aggregate, is useful work GTD - GAS-TURBINE ENGINE.

The useful work Le, in reference to 1 tog of working medium, is equal to the difference between work Lt, developed by turbine with the expansion in it of gas, and work L_K, expended by compressor to the compression in it of air. Graphically operating cycle GTD - GAS-TURBINE ENGINE can be represented in the R.V- diagram, where R - pressure, V - volume (Fig. 2). The higher efficiency of compressor and turbine, the less L_K and the greater Z_T, i.e. useful work increases. An increase in the temperature of the gas before the turbine also contributes to an increase in the useful work L₁, (line of e'ya ' in Fig. 2). Efficiency GTD - GAS-TURBINE ENGINE is characterized by its effective efficiency, which is the ratio of useful work to a quantity of heat, spent on the creation of this work.

In the contemporary. GTD - GAS-TURBINE ENGINE efficiency of compressors and turbines respectively composes 0,88-0,9 and 0,9-0,92. The rate -.pa of the gas before the turbine in transport and stationary GTD - GAS-TURBINE ENGINE is 1100-1200 k, and in the aviation it achieves 1600 K. achyuiyevement such temperatures became possible because of the production of details GTD - GAS-TURBINE ENGINE from the high-temperature (strength) materials and application of cooling his elements. At the perfection of flow area reached and the temperature of gases 1000 to efficiency of the engine, which works according to the simplest diagram, do not exceed 25%. For increasing efficiency the heat-, that is contained in the gas outgoing from the turbine, is used in the operating cycle GTD - GAS-TURBINE ENGINE for preheating the compressed air, which enters the combustion chamber. Heat exchange between the waste gas and the compressed air, which enters the combustion chamber, occurs in the regenerative heat exchangers, and the working process GTD - GAS-TURBINE ENGINE, in which is utilized the heat- outgoing from the turbine gases, NAZ by regenerative. To increase efficiency contribute also preheating gas in the process of its expansion in the turbine, together with the use of heat of the outgoing gases, and cooling air in the process of its compression in the compressor (Fig. 3). In this case useful work grows because of an increase in work Lm, developed by turbine, and to the decrease of work Lk, consumed by compressor. The schematic of such a GTD - GAS-TURBINE ENGINE into the 30's was proposed by Sov. scientific G. i. zotikov. Compressor and low-pressure turbine are located on one shaft, which is not connected with the drive shaft, for example, generator, screw propeller. Their frequency of rotation can change in the dependence on the operating mode, which substantially improves efficiency GTD - GAS-TURBINE ENGINE with the light loads.

Fig. 3. Schematic of gas turbine engine with the heat recovery, cooling of air in the process of compression and preheating the gas in the process of the expansion: 1 - starting motor: 2, 3, 4 - compressors of low, average and high pressure; 5 combustion chamber; b, 7 turbine of high and low pressure; 8- regenerator; 9 cooler of air.

GTD - GAS-TURBINE ENGINE can work on the gaseous fuel (natural gas, following and side-line combustible gases, gas-producing gases, gases of blast and carbon black furnaces and subterranean gasification); on the liquid propellant (kerosene, gas oil, diesel fuel, petroleum residue); solid fuel (carbon and peat dust). Heavy liquid and solid propellants find use in GTD - GAS-TURBINE ENGINE, which work on the semiclosed and closed cycle (Fig. 4). In GTD - GAS-TURBINE ENGINE of closed cycle working the body after the accomplishment of work in the turbine is not ejected, but it participates in the following cycle. Such GTD - GAS-TURBINE ENGINE make it possible to increase single power and to use nuclear fuel in them. GTD - GAS-TURBINE ENGINE found wide application in the aviation (see aircraft engine) as osn of the engines of the power plants of aircraft, helicopters, unmanned flying vehicles and the like GTD - gas-turbine engine they use at the thermal power stations for the drive of electric generators; at the mobile electric generators, for example in the mobile power plants; for the drive of compressors (air and gas) with the simultaneous production of elektrich. and thermal energy in the petroleum, the gas, the metallurg.. and chem. industry; as the traction engines of gas turboelectric locomotives, buses, of passenger cars and trucks, of caterpillar tractors, tanks; as the power plants of ships, launches, of submarines and for the drive of vspomogat. of machines and mechanisms (winches, pumps and of others.); on the objects of military equipment as energetich. and tractive power plants. The field of application OF GTD - GAS-TURBINE ENGINE is enlarged. In 1956 power GTD - GAS-TURBINE ENGINE in entire peace were 900 MW, to 1958 it exceeded 2000 MW, and to the beginning. 1968 it reached 40 000 MW (without aviation and military equipment). The greatest single power produced in THE USSR GTD - GAS-TURBINE ENGINE is 100 MW (1969). Effective efficiency of engines - 35% reached.

Fig. 4. Schematic of the gas turbine engine, which works on the closed cycle: 1 - surface heater; 2 - turbine; 3 - compressor; 4- cooler; 5 - regenerator; 6- storage battery of air; 7 auxiliary compressor.

Development GTD - GAS-TURBINE ENGINE follows the path of improving of its elements (compressor, turbine, combustion chamber, heat exchangers, etc.), increase in temperature and gas pressure before the turbine, and also the application of the kombinirovannykh power plants with the steam turbines and the free-piston generators of gas. The operation of such installations in stationary power engineering and in the field of transportation showed that with the utilization of the heat of waste gas and the high perfection of basic elements their effective efficiency it reaches 42-45%.

Lit.: Bikchentay R. n., Lopoyan G. S., Porshakov b. p., the application of gas-turbine units in the industry, M., 1959; Losses on boiling V. V. and Chernobrovkin a. p., gas turbines, M., 1960; Shnee 4. i., gas turbines, M., 1960; Bases of design and characteristic of gas turbine engines, [ translated from English ], M., 1964; Gas-turbine units. Atlas of constructions and diagrams, M, 1967; Simmons S. R, GaS turbine manual, L, 1968.

See also it is cast. with st. Aviation gas turbine. S. 3. Kopelev.