# US 5,343,690 A · Starting of a small turbojet

> Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt

- Number: US 5,343,690 A
- Document ID: US5343690A
- Status: Granted
- Kind: A
- Application number: 08/033,170
- Filed: 1993-03-16
- Granted: 1994-09-06
- Earliest claimed: 1990-11-09
- Assignees: Sundstrand Corporation
- Inventors: Jack R. Shekleton; Colin Rodgers
- Web page: https://patentgrep.com/patent/US5343690A

## CPC

- F02C 3/05: the compressor and the turbine being of the radial flow type
- F01D 5/284: {Selection of ceramic materials}
- F02C 7/272: generated by cartridges
- F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00)
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)

## Abstract

Difficulties in starting a turbine engine, particularly ones having a small volume combustor (83) with a low dome height, may be avoided by a method including the steps of a) forming the turbine engine compressor (48) of a low density, high temperature resistant ceramic material, b) directing pyrotechnic gases at a temperature of at least about 3,000.degree. F. against the blades (48) of the compressor, c) continuing the step of directing until the turbine rotor (44) is rotating at at least about 60 percent of rated speed and d) combusting fuel in the combustor (83) of the turbine engine to maintain the rotor (44) rotating at at least about 60 percent of rated speed.

## Claims

### Claim 1

A method of starting a turbine engine having a rotor, a combustor for supplying hot gases to cause rotation of said rotor, a rotatable compressor for supplying gases to said combustor, said compressor having a plurality of blades extending outwardly therefrom, a fuel source for supplying fuel to said combustor, comprising:
a) prior to operation of said turbine engine, forming at least said blades of the compressor of ceramic material;
b) thereafter, directing pyrotechnic gases having a temperature of at least about 3,000.degree. F. and a supersonic velocity against said blades of the compressor until said rotor has reached a predetermined rotational speed;
c) introducing fuel into said combustor and igniting that fuel to cause combustion to produce said hot gases; and
d) continuing said combustion to maintain said predetermined rotational speed of said rotor after said directing of pyrotechnic gases ceases.

### Claim 2 (depends on 1)

The method according to claim 1 wherein said pyrotechnic gases are also directed into said combustor to cause said igniting of fuel.

### Claim 3

A method of starting a turbine engine having a rotor, a combustor means for supplying hot gases to cause rotation of said turbine rotor, a rotatable compressor means for supplying gases to said combustor means and a fuel supply means for providing fuel to said combustor means for combustion therein upon mixing with said gases from said compressor means, comprising the steps of:
a) initially directing pyrotechnic gases at said compressor means so as to cause rotation of said compressor means;
b) thereafter, directing said pyrotechnic gases into said combustor means so as to cause ignition of said fuel therein to begin combustion to supply hot gases to said turbine rotor sufficient to cause rotation thereof; and
c) continuing to direct said pyrotechnic gases at said compressor means until said turbine rotor is rotating at a predetermined speed, that speed being sufficient to maintain stable combustion within said combustor without use of said pyrotechnic gases.

### Claim 4 (depends on 3)

The method of claim 3 wherein said pyrotechnic gases are directed against the compressor means at a supersonic velocity.

### Claim 5 (depends on 3)

The method of claim 3 wherein said compressor means and said turbine rotor are integrally formed as a monorotor structure.