Spytek Aerospace Corp.

450 Frontier Way, Unit D
Bensenville, IL 60106
7 Employees

SBIR Award Summary

Total Number of Awards 9
Total Value of Awards $3.02MM
First Award Date 04/03/07
Most Recent Award Date 10/23/14

Key Personnel

Last Name Name Awards Contact
Spytek Mr. Christopher Spytek 9 Message
Spytek Elizabeth Spytek 0 Message

9 Awards Won

Phase 2 SBIR

Agency: Air Force
Topic: AF131-160
Budget: 10/23/14 - 01/20/17

ABSTRACT: With the roll of UAV s becoming more complex, and their use more widespread, tactical requirements for performance, reliability, maintainability, supportability, and most recently low cost, have created the need for an advanced cycle propulsion system. Such an engine, must address the conflicting requirements, of large amounts of elect...

Phase 1 SBIR

Agency: Air Force
Topic: AF131-160
Budget: 07/25/13 - 02/25/14

ABSTRACT: There is an urgent Air Force need for an advanced cycle turbo-fan for UAV applications. Spytek Aerospace proposes a 2-ITB, 500 LBT turbo-fan engine equipped with ITB driven fan capable of running a generator, thru a second ITB in variable modes for additional power on demand and at high altitude. Northrop Grumman has indicated signifi...

Phase 1 SBIR

Agency: Navy
Topic: N112-096
Budget: 10/18/11 - 04/18/12

The need to optimize gas turbine engine performance, coupled with electrification of aircraft systems, as on the Lockheed F35 and Boeing 787 , in order to maximize efficiency and flexibility, created an opportunity to develop a smart electrically driven lubrication system for gas turbine engines. Spytek s electric oil system ascertains the o...

Phase 1 SBIR

Agency: Navy
Topic: N092-122
Budget: 11/17/09 - 06/30/10

Our twin spool Inter Turbine Burner (ITB) equipped turbine engine is throttleable between 50 Hp to 700 Hp with a weight-to-power ratio (including gearbox) approaching .50 and possesses multi-fuel capability. A demonstration of this unique turbine technology, hybrid capable, marine applications is proposed. The Phase I TRL4 demonstration will inc...

Phase 2 SBIR

Agency: Office of the Secretary of Defense
Topic: OSD07-ES9
Budget: 06/05/08 - 06/05/10

Advanced turbojet and turboshaft engines will be required to support future Unmanned Air Vehicle (UAV) missions which require a significant amount of time at cruise conditions to achieve a primary objective of increased range and time-on-station. Inter Turbine Burner (ITB) technology is the most promising method of improving mission integrated ...

Phase 2 SBIR

Agency: Air Force
Topic: AF071-179
Budget: 06/05/08 - 10/05/10

Spytek Aerospace will soon become a low cost supplier of small high performance gas turbines for expendable UAV military operations, university research centers and hobbyists. During Phase I Spytek Aerospace analytically examined and experimentally assessed two `swirl-maintained' diffuserless high g combustor designs in our ATG-2 combustion rig...

Phase 1 SBIR

Agency: Office of the Secretary of Defense
Topic: OSD08-UM5
Budget: 05/28/08 - 11/28/08

The ever increasing utilization of unmanned air, ground and maritime vehicles has dictated the need for the DoD to more effectively integrate the generation of electrical power with the propulsion engine associated with unmanned vehicles. This issue applies equally to turbine and IC engines. The problem could be considered more vexing in the c...

Phase 1 SBIR

Agency: Office of the Secretary of Defense
Topic: OSD07-ES9
Budget: 05/11/07 - 05/11/08

Gas turbine engines using multistage turbine sections have the inherent disadvantage of temperature loss through the turbine section. This occurs when each successive turbine stage extracts energy from the superheated mass airflow. The result is limited energy potential due to the first stage turbine temperature limits. An inter-turbine burne...

Phase 1 SBIR

Agency: Air Force
Topic: AF071-179
Budget: 04/03/07 - 01/03/08

The recent incorporation of high g combustor designs in gas turbine engines at Spytek Aerospace has presented the need for the further optimization of the compressor/combustor interface (i.e. diffuser). Legacy combustor designs remove the inherent swirl out of the gas stream at the compressor exit, introducing aerodynamic losses and structural ...